# LANDING GEAR - REPLACEMENT OF MAIN LANDING GEAR RETRACTION ACTUATOR 1. PLANNING INFORMATION A. SB EFFECTIVITY Aircraft affected: MODEL SN Embraer 190( ) and 195( ) 19000002, 19000004, 19000006 thru 19000108, 19000110 thru 19000139, 19000141 thru 19000158, 19000160 thru 19000176, 19000178 thru 19000202, 19000204 thru 19000224, 19000226 thru 19000235, 19000237 thru 19000242, 19000244 thru 19000260, 19000262 thru 19000277, 19000279 thru 19000295, 19000297 thru 19000306, 19000308 thru 19000316, 19000318 thru 19000324, and 19000326 thru 19000339, 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( ) and 195( ) model aircraft SN 19000001, 19000003, 19000005, 19000325, 19000340 and on, have an equivalent modification factory-incorporated. 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 1 of 85 Embraer Copyright © 2010. All rights reserved.

# B. CONCURRENT REQUIREMENTS None. C. REASON (1) HISTORY The retraction actuator PN 190-70980-403 failed during qualification tests as below: – 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 undammped extension, resulting in rupture also in the side stay, losing the 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 caused economic consequences. (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. 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 2 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# 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. The replacement of the retraction actuator requires that the attaching point of the main fitting be also 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 temporary modification until Part III is 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

. 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 3 Embraer Copyright © 2010. All rights reserved.

# 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 until Part III is accomplished. 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 consisting in the bushing replacement described at Liebherr-Aerospace SB 32-11-190-MLG-03, attached at the 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 that 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). 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 4 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# 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. (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. 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 5 Embraer Copyright © 2010. All rights reserved.

# (3) APPLICABLE TO PART III – Access opening: None. – Inspection: None. – Modification: 4.0 man-hours. – Access closure: None. – 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 (a) Applicable to Embraer 190 – Change in basic weight: + 0.805 lb (+ 0.365 kg). – Change in basic moment: + 591.390 lb.in (+ 6.811 kg.m). (b) Applicable to Embraer 195 – Change in basic weight: + 0.805 lb (+ 0.365 kg). – Change in basic moment: + 617.061 lb.in (+ 7.107 kg.m). (2) APPLICABLE TO PART II (a) Applicable to Embraer 190 – Change in basic weight: + 0.805 lb (+ 0.365 kg). – Change in basic moment: + 591.390 lb.in (+ 6.811 kg.m). (b) Applicable to Embraer 195 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 6 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# – Change in basic weight: + 0.805 lb (+ 0.365 kg). – Change in basic moment: + 617.061 lb.in (+ 7.107 kg.m). (3) APPLICABLE TO PART III (a) Applicable to Embraer 190 – Change in basic weight: + 1.610 lb (+ 0.730 kg). – Change in basic moment: + 1182.78 lb.in (+ 13.622 kg.m). (b) Applicable to Embraer 195 – 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 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. AMM 190/( ) Aircraft Maintenance Manual PART II - 32-00-00 and 32-31-01 - LANDING GEAR. K. OTHER PUBLICATIONS AFFECTED AIPC 190/( ) Aircraft Illustrated Parts Catalog - 32-11-01 - LANDING GEAR. 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 7 Embraer Copyright © 2010. 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 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.: 190-32-0037 PAGE: 8 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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 to material necessary to modify each main landing gear (MLG) shock strut; 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 9 Embraer Copyright © 2010. 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 to 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 to 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.: 190-32-0037 PAGE: 10 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 11 Embraer Copyright © 2010. 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.: 190-32-0037 PAGE: 12 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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 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 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 13 Embraer Copyright © 2010. 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.: 190-32-0037 PAGE: 14 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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 fleet.reliability@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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 15 Embraer Copyright © 2010. All rights reserved.

# 4. APPENDIX 1 SB 32-11-190-MLG-05 - RETRACTION ACTUATOR ATTACHMENT POINT - TEMPORARY MODIFICATION 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 16 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN



### MAIN LANDING GEAR – RETRACTION ACTUATOR ATTACHMENT POINT - TEMPORARY MODIFICATION

1. P L A N N I N G I N F O R M A T I O N A. E F F E C T I V I T Y 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. C O N C U R R E N T R E Q U I R E M E N T S None C. R E A S O N 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 fi tting is also replaced. D. D E S C R I P T I O N This Service Bulletin describes the procedure to modify the RA attachment point: – Washer and sleeve on the main fi tting. – 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 fi nal solution (SB 32-11-190-MLG-03) must be applied during the next shop visit.

I nitial Issue : Sep 20/10 

# 3 2-11-190-MLG-05 R evision 0 : Sep 20/10 P age 1 of 12 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 17 Embraer Copyright © 2010. 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. C O M P L I A N C E This Service Bulletin can be performed at any time. F. A P P R O V A L Government or other regulatory agency approval of this Service Bulletin is Embraer’s responsibility. G. M A N P O W E R – Modi fi cation of the RA Attachment point: 1 manhours 1 mechanic H. W E I G H T A N D B A L A N C E None I. S O F T W A R E A C C O M P L I S H M E N T S U M M A R Y None J. R E F E R E N C E S 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. P U B L I C A T I O N S A F F E C T E D 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.: 190-32-0037 PAGE: 18 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

2. M A T E R I A L I N F O R M A T I O N A. M A T E R I A L
- P R I C E A N D A V

A I L A B I L I T Y (1) A modi fi cation 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 modi fi cation 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 19 Embraer Copyright © 2010. 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.: 190-32-0037 PAGE: 20 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

B. I N D U S T R Y S U P P O R T I N F O R M A T I O N Not applicable C. M A T E R I A L N E C E S S A R Y F O R E A C H A I R C R A F T Refer to the associated Embraer airframe Service Bulletin. D. M A T E R I A L N E C E S S A R Y F O R E A C H C O M P O N E N T (1) MODIFICATION KIT (a) Modi fi cation Kit PN 4259A8800-01: Each modi fi cation 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 Identi fi cation 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 21 Embraer Copyright © 2010. 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* PR1826B2ALO-1/2
- AR 6* Sealant 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.: 190-32-0037 PAGE: 22 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

E. R E
- I D E N T I F I E D P A R T S Reidenti fi ed 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 identi fi cation plate is introduced. F. T O O L I N G
- P R I C E A N D A V

A L A B I L I T Y 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 23 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

3. A C C O M P L I S H M E N T I N S T R U C T I O N S A. P R O C E D U R E W

A R N I N G : 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. N O T E : 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 fi nish applied, refer to fi gure 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 identi fi cation 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 fi tting.

Initial Issue : Sep 20/10 

# 32-11-190-MLG-05 Revision 0 : Sep 20/10 Page 8 of 12 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 24 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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. N O T E : Make sure that no air bubbles are between the new plate and the main fi tting. (f) Use an Cleaning Agent and remove the unwanted sealant. (g) Use tape to attach the new plate (6) to the main fi tting until the sealant dry. N O T E : 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 fi tting. (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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 25 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320062.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.: 190-32-0037 PAGE: 26 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320063.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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 27 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320066.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-Identi fi cation 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.: 190-32-0037 PAGE: 28 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# 4. APPENDIX 2 SB 32-11-190-MLG-03 - RETRACTION ACTUATOR ATTACHMENT POINT - FINAL MODIFICATION 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 29 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN



### MAIN LANDING GEAR – RETRACTION ACTUATOR ATTACHMENT POINT - FINAL MODIFICATION

1. P L A N N I N G I N F O R M A T I O N A. E F F E C T I V I T Y 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. C O N C U R R E N T R E Q U I R E M E N T S None C. R E A S O N 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 fi tting attachment are also replaced. D. D E S C R I P T I O N This Service Bulletin describes the procedure to replace the retraction actuator attachment: – Bushings on the main fi tting. – 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).

I nitial Issue : Sep 27/10 

# 3 2-11-190-MLG-03 R evision 0 : Sep 27/10 P age 1 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 30 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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. C O M P L I A N C E This Service Bulletin can be performed at any time, and should be performed at the latest during fi

rst overhaul (20,000 Flight Cycles). F. A P P R O V A L Government or other regulatory agency approval of this Service Bulletin is Embraer’s responsibility. G. M A N P O W E R – Removal of the old bushings: 0.5 manhours 1 mechanic – Installation of the new bushings: 2 manhours 1 mechanic H. W E I G H T A N D B A L A N C E None I. S O F T W A R E A C C O M P L I S H M E N T S U M M A R Y None J. R E F E R E N C E S 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. P U B L I C A T I O N S A F F E C T E D 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 31 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

2. M A T E R I A L I N F O R M A T I O N A. M A T E R I A L
- P R I C E A N D A V

A I L A B I L I T Y (1) The table below shows the bushings modi fi cation kit which is applicable to the serial number of the MLG Shock Strut. Bushings Modi fi cation 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.: 190-32-0037 PAGE: 32 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

Bushings Modi fi cation 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. N O T E : 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 modi fi cation kits and bolts will be supplied Free-Of-Charge (FOC). The FOC conditions are limited to 20,000 Flight Cycles or the fi rst overhaul (whichever comes fi rst). (4) The bushings modi fi cation 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 33 Embraer Copyright © 2010. 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.: 190-32-0037 PAGE: 34 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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. I N D U S T R Y S U P P O R T I N F O R M A T I O N Not applicable C. M A T E R I A L N E C E S S A R Y F O R E A C H A I R C R A F T Refer to the associated Embraer airframe Service Bull etin. D. M A T E R I A L N E C E S S A R Y F O R E A C H C O M P O N E N T (1) MODIFICATION KIT (a) Modi fi cation Kit PN 4259A8100-01: Each modi fi cation kit PN 4259A8100-01 contains th e 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 bear ing 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 35 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

(b) Modi fi cation Kit PN 4259A8200-01: Each modi fi cation 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.: 190-32-0037 PAGE: 36 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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* PR1826B2ALO-1/2
- AR 6* Sealant PR1826B2ALO-1/4
- AR 6* This table does not reference the consumables need ed 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 37 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

E. R E
- I D E N T I F I E D P A R T S Reidenti fi ed 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. T O O L I N G
- P R I C E A N D A V

A L A B I L I T Y 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/Installatio n Tool 1

- 2821A0100-03W08 Bore Reamer 1

- 2821A0100-03W01 Flange Reamer 1* This table does not reference the speci fi cs tools needed to perform the standard procedures. For the standard procedures refer to these procedures. * Optional (If a machine of the bushing fl ange 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.: 190-32-0037 PAGE: 38 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

3. A C C O M P L I S H M E N T I N S T R U C T I O N S A. P R O C E D U R E W

A R N I N G : 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. N O T E : 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 fl anges. 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 fl anges 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). N O T E : 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 39 Embraer Copyright © 2010. 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). 1 0 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 fl anges. 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). N O T E : 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). 1 0 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. N O T E : This step is only necessary if you use the modi fi cation 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 fi tting: (a) Use an Abrasive Cloth to make the surface of the bores and of the fl anges smooth. (b) Use approved Cleaning Agent to remove the sealant and to clean the surface of the bores and of the fl anges.

Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 11 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 40 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

(c) Do a visual inspection for cracks: – If you fi nd any cracks replace the MLG Shock Strut. (d) Do an inspection of the bores and the fl anges, refer to INSPECTION OF THE BORES AND THE FLANGES, Page 29. W

A R N I N G : 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 fl anges around the bores of the main fi tting. (b) Installation of the Bushing (8): N O T E : 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). C A U T I O N : 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. N O T E : 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).

Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 12 of 39 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 41 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

(d) Machine and Installation of the Bushing (9): N O T E : The installation of the bushing must be a wet-installation. Do not let the primer paint on the bushing dry before to install it. C A U T I O N : 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 fl ange of the bushing (8) and the opposite lower point of the fl ange of the retraction actuator attachment. 2 Machine the fl ange 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). C A U T I O N : 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. N O T E : 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). N O T E : 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: N O T E : You must use the Flange Reamer - PN 2821A0100-03W01 to do this procedure. N O T E : 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.

Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 13 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 42 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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). C A U T I O N : 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. N O T E : 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 fl anges 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). N O T E : 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 fl ange 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). N O T E : Do step (e) when the pressure to the reamer is not suf fi cient. g Release the reamer (fr4). h Remove the guide (fr2). i Hold the reamer (fr4) between the two fl anges and remove the bolt (fr1) with the hand wheel (fr3) and the guide (fr2).

Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 14 of 39 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 43 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

j Remove the reamer (fr4). k Use an Abrasive Cloth to make the edges of the bush (9) smooth. W

A R N I N G : USE EAR PROTECTION DURING ALL THE PROCEDURE. LOUD NOISES CAN CAUSE INJURY TO YOUR EARS. C A U T I O N : DO NOT TURN THE REAMER IN A COUNTERCLOCKWISE DIRECTION EVEN TO REMOVE THE REAMER. YOU CAN DAMAGE THE BLADES OF THE REAMER. C A U T I O N : 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). C A U T I O N : 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. N O T E : 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 fl anges surfaces from chips of metal. (g) Apply a bead of sealant PR1826B2ALO around the joint of the bushings and the main fi tting. (h) Make sure that the bolt (5) has the Xylan surface fi nish applied, refer to fi gure 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).

Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 15 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 44 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

(4) Change the identi fi cation information on the MLG identi fi cation 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 45 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320041.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
Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 17 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 46 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320058.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 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 47 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320059.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
Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 19 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 48 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320042.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
Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 20 of 39 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 49 Embraer Copyright © 2010. 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 fr5 fr4 fr3 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
Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 21 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 50 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320057.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
Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 22 of 39 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 51 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320043.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"

Identi fi cation FIGURE 3
Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 23 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 52 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

This page intentionally left blank.

In itial Issue : S ep 27/10 

# 32 -11-190-MLG-03 Re vision 0 : S ep 27/10 Pa ge 24 of 39 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 53 Embraer Copyright © 2010. 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: N O T E : 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 fl anges. (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. N O T E : 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 Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 25 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 54 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

(2) Installation of the Bushing (9), refer to Figure 4, Sheet 2: N O T E : 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 fl anges. (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. N O T E : 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 Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 26 of 39 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 55 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320060.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 Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 27 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 56 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETINLB190SB320061.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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 57 Embraer Copyright © 2010. 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 fl anges 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 fl anges. N O T E : 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.: 190-32-0037 PAGE: 58 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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 fi nd 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 59 Embraer Copyright © 2010. 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 speci fi cations. 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: N O T E : 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 fl anges sides besides the condition above the width of the fl ange 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.: 190-32-0037 PAGE: 60 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

(2) Bore Tolerance Check: N O T E : 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. N O T E : 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 61 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

E. BORE TOLERANCES REPAIR, refer to Figure 5. N O T E : 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 fi nal 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. N O T E : 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.: 190-32-0037 PAGE: 62 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

4mm 3mm FOR THE BORE 6mm FOR THE FLANGE

3mm 3mm 0.2mmLB190SB320056.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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 63 Embraer Copyright © 2010. All rights reserved.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

dLB190SB320055.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 Initial Issue : Sep 27/10 

# 32-11-190-MLG-03 Revision 0 : Sep 27/10 Page 35 of 39 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 64 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

This page intentionally left blank.

LOC AL REPAIR PROCEDURE In itial Issue : S ep 27/10 

# 32 -11-190-MLG-03 Re vision 0 : S ep 27/10 Pa ge 36 of 39 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 65 Embraer Copyright © 2010. 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.: 190-32-0037 PAGE: 66 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

(2) Procedure: C A U T I O N : 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). N O T E : 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. N O T E : 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 67 Embraer Copyright © 2010. All rights reserved.SERVICE BULLETIN

D. FLANGE REPAIR C A U T I O N : 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. C A U T I O N : 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 fl ange 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 fl ange 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 fl ange refer to the standard procedure MIL-STD-1949. – A Temper Etch Inspection Test on the fl ange refer to the standard procedure MIL-STD-867. (3) Flap-peen the fl ange, refer to the standard procedure MIL-R-81841. N O T E : 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. N O T E : 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.: 190-32-0037 PAGE: 68 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. 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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 69 Embraer Copyright © 2010. 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

SB No.: 190-32-0037 PAGE: 70 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 71 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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

SB No.: 190-32-0037 PAGE: 72 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 73 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

DATE: 06/SEP/2010 

# 190-70980-32-02 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 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 74 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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. 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 75 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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

SB No.: 190-32-0037 PAGE: 76 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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. 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 77 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

DATE: 06/SEP/2010 

# 190-70980-32-02 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. 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 78 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

DATE: 06/SEP/2010 

# 190-70980-32-02 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. 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 79 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

DATE: 06/SEP/2010 

# 190-70980-32-02 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. 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 80 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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. 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 81 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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

SB No.: 190-32-0037 PAGE: 82 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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) 

# SERVICE BULLETIN

DATE: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 83 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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) 

# SERVICE BULLETIN

SB No.: 190-32-0037 PAGE: 84 DATE: 06/Oct/2010 REVISION No.: Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN

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: 06/Oct/2010 REVISION No.: SB No.: 190-32-0037 PAGE: 85 Embraer Copyright © 2010. All rights reserved.

# SERVICE BULLETIN EVALUATION
THE PURPOSE OF THIS FORM IS TO COLLECT DATA THAT WILL BE USED TO IMPROVE THE QUALITY OF OUR SERVICE BULLETINS AND UPDATE THE TECHNICAL PUBLICATIONS. PLEASE FILL IN FORM AND RETURN IT TO: EMBRAER - EMPRESA BRASILEIRA DE AERONÁUTICA S.A. EFTC - SERVICE BULLETIN ENGINEERING AV. BRIGADEIRO FARIA LIMA, 2170 SÃO JOSÉ DOS CAMPOS - SP - 12227-901 BRASIL Fax: + 55 12 3927-6600 (ext. 1624) e-mail: fleet.reliability@embraer.com.br 

## S.B. Title: S.B.: (Number / Rev.) Operator: SB Implementation Report Aircraft Serial Number or Registration Number: Incorporation Date: Aircraft Flight Hours: Aircraft Landings:
POST-ACCOMPLISHMENT EVALUATION: (Check applicable squares below) 

### ESTIMATED MANPOWER: [ ] OK [ ] NOT OK (Explain Below) MATERIAL & KITS: [ ] OK [ ] NOT OK (Explain Below) ACCOMPLISHMENT INSTRUCTIONS: [ ] OK [ ] NOT OK (Explain Below) FIGURES: [ ] OK [ ] NOT OK (Explain Below) SB GENERAL EVALUATION: [ ] OK [ ] NOT OK (Explain Below) COMMENTS: (Bulletin quality/ Difficulties found at the time of incorporation/ Suggested improvements/ Other)

Organization: Fax: Phone: E-mail: Address: Prepared by:(Name/Title) Date:



## Embraer Copyright © 2010. All rights reserved.