# Embraer Service Bulletin 190-57-0056 ## Copies (3) Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist. - No revision named ("SB190-57-0056 --"), 150 pages: PDF https://openairdocs.org/files/sha256/7b/2f/7b2f11be73fa7e2ef70919ab7422c8fe71ac5e5db2ff5b67297740dd0f480448; text https://openairdocs.org/service-documents/embraer/sb-190-57-0056/file/7b2f11be73fa.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2019-0701; AD 2020-04-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. - No revision named, part 1 of 2 ("SB 190-57-0056 - Original Revision_Part1"), 60 pages: PDF https://openairdocs.org/files/sha256/a8/d8/a8d81e87cc632beb049844244399d7b9fad0e0903e0056c74f8c4f82e36ae8b3; text https://openairdocs.org/service-documents/embraer/sb-190-57-0056/file/a8d81e87cc63.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2023-1635, the docket of AD 2023-21-11. Not covered by OpenAirDocs’ CC0 dedication. - No revision named, part 2 of 2 ("SB 190-57-0056 - Original Revision_Part2"), 53 pages: PDF https://openairdocs.org/files/sha256/37/6c/376c04542e06651769b46c6c626b7746782edc82c5fa94b5b0e8623f5f86267b; text https://openairdocs.org/service-documents/embraer/sb-190-57-0056/file/376c04542e06.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2023-1635, the docket of AD 2023-21-11. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Embraer](https://openairdocs.org/service-documents/embraer.md) - Type: Service bulletin (Service Bulletin) - Number: 190-57-0056 - Page: https://openairdocs.org/service-documents/embraer/sb-190-57-0056 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2020-04-16](https://openairdocs.org/ad/2020-04-16.md), effective May 7, 2020: No revision named Also cited in [4 difficulty reports](https://openairdocs.org/service-documents/embraer/sb-190-57-0056/reports.md). ## Text (150 pages) No revision named, the newest copy. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2019-0701; AD 2020-04-16 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 WINGS - LH/RH WING LOWER SKIN PANEL - REINFORCEMENT In connection with the use of this document, Embraer does not provide any express or implied warranties and expressly disclaims any warranty of merchantability or fitness for a particular purpose. This document contains trade secrets, confidential, proprietary information of Embraer and technical data subject to U.S. Expor t Administration Regulation ("EAR") and other countries export control laws and regulations. Diversion contrary to the EAR and other laws and regulations is strictly forbidden. The above restrictions may apply to data on all pages of this document. 1. PLANNING INFORMATION A. SB EFFECTIVITY Aircraft affected: MODEL SN Embraer 190( ) and 195( ) 19000001, 19000003, 19000004, and 19000006 thru 19000077. In-production effectivity: This bulletin does not affect any in-production aircraft. B. CONCURRENT REQUIREMENTS None. C. REASON (1) HISTORY Embraer has received reports about crack detected in the wing lower skin at stringer run-out (stringer #20, close to the rib 9), on the Left-Hand (LH) and Right-Hand (RH) wings. The cracks propagation on these wing lower skin stringers may result in fuel leakage and reduced wing structural integrity. A stress concentration at the region of the stringer run-out was identified as the root cause. (2) OBJECTIVE To provide the instructions to install doublers reinforcement on the wing forward and rear lower skin panel and to do cold expansion of some holes, on the Left-Hand (LH) and Right-Hand (RH) wings. (3) EXPECTED BENEFITS This modification is aimed at preventing premature cracks at the region of the wing lower skin run-outs, reducing the stress concentration, and improving the aircraft economical fatigue life. (4) REVISION HISTORY None. D. DESCRIPTION This Bulletin is divided into 4 PARTS, as follows: PART I LH WING FORWARD LOWER SKIN PANEL - REINFORCEMENT Applicable to: Refer to 1.A. SB EFFECTIVITY SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 1 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 2 CAUTION: WHEN YOU START THE MODIFICATION RELATED TO PART I OF THIS SERVICE BULLETIN, YOU MUST COMPLETE IT BEFORE YOU START THE MODIFICATION RELATED TO PART II. The modification described in PART I of this bulletin consists of reinforcing the LH wing forward lower skin panel by doing the cold expansion of some holes and installing doublers reinforcement. To do this, it is necessary to get access to the LH pylon area and: – Defueling the aircraft tank. – Removing the LH pylon forward fairings, LH pylon side fairings, LH pylon aft fairings, LH thrust reverser, LH engine, and access panel 521EB. – Releasing from their attaching points the applicable parts (firewall hydraulic shutoff valve, clamp shells of the tubes, electrical harness, fuel and hydraulic tubes, the parts of the anti-icing leak detectors, the existing bonding jumpers and the bleed duct). – Lowering the LH pylon. PART II LH WING REAR LOWER SKIN PANEL - REINFORCEMENT Applicable to: Refer to 1.A. SB EFFECTIVITY CAUTION: WHEN YOU START THE MODIFICATION RELATED TO PART II OF THIS SERVICE BULLETIN, YOU MUST COMPLETE IT BEFORE YOU START THE MODIFICATION RELATED TO PART I. The modification described in PART II of this bulletin consists of reinforcing the LH wing rear lower skin panel by doing the cold expansion of some holes and installing doublers reinforcement. To do this, it is necessary to get access to the LH pylon area and: – Defueling the aircraft tank. – Removing the LH pylon forward fairings, LH pylon side fairings, LH pylon aft fairings, LH thrust reverser, LH engine, and access panel 521EB. – Releasing from their attaching points the applicable parts (firewall hydraulic shutoff valve, clamp shells of the tubes, electrical harness, fuel and hydraulic tubes, the parts of the anti-icing leak detectors, the existing bonding jumpers and the bleed duct). – Lowering the LH pylon. PART III RH WING FORWARD LOWER SKIN PANEL - REINFORCEMENT Applicable to: Refer to 1.A. SB EFFECTIVITY CAUTION: WHEN YOU START THE MODIFICATION RELATED TO PART III OF THIS SERVICE BULLETIN, YOU MUST COMPLETE IT BEFORE YOU START THE MODIFICATION OF PART IV. The modification described in PART III of this bulletin consists of reinforcing the RH wing forward lower skin panel by doing the cold expansion of some holes and installing doublers reinforcement. To do this, it is necessary to get access to the RH pylon area and: – Defueling the aircraft tank. SERVICE BULLETIN SB190-57-0056 Page 2 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 3 – Removing the RH pylon forward fairings, RH pylon side fairings, RH pylon aft fairings, RH thrust reverser, RH engine, and access panel 621EB. – Releasing from their attaching points the applicable parts (firewall hydraulic shutoff valve, clamp shells of the tubes, electrical harness, fuel and hydraulic tubes, the parts of the anti-icing leak detectors, the existing bonding jumpers and the bleed duct). – Lowering the RH pylon. PART IV RH WING REAR LOWER SKIN PANEL - REINFORCEMENT Applicable to: Refer to 1.A. SB EFFECTIVITY CAUTION: WHEN YOU START THE MODIFICATION RELATED TO PART IV OF THIS SERVICE BULLETIN, YOU MUST COMPLETE IT BEFORE YOU START THE MODIFICATION OF PART III. The modification described in PART IV of this bulletin consists of reinforcing the RH wing rear lower skin panel by doing the cold expansion of some holes and installing doublers reinforcement. To do this, it is necessary to get access to the RH pylon area and: – Defueling the aircraft tank. – Removing the RH pylon forward fairings, RH pylon side fairings, RH pylon aft fairings, RH thrust reverser, RH engine, and access panel 621EB. – Releasing from their attaching points the applicable parts (firewall hydraulic shutoff valve, clamp shells of the tubes, electrical harness, fuel and hydraulic tubes, the parts of the anti-icing leak detectors, the existing bonding jumpers and the bleed duct). – Lowering the RH pylon. NOTE: The modification presented in this bulletin affects Fatigue Critical Structure (FCS) and change(s) to the related Damage Tolerance Inspection (DTI) instructions is (are) required. Refer to Damage Tolerance Inspection (DTI) instructions described in Airworthiness Limitation Requirements in the Maintenance Review Board Report (MRBR). E. COMPLIANCE (1) APPLICABLE TO PART I Embraer recommends the accomplishment of PART I of this bulletin in the next 6,250 Flight Cycle(s) or 7,500 Flight Hour(s) from the first issue date of this bulletin, whichever occurs first. NOTE: 1) According to the WFD regulation (§26.21), for aircraft under ANAC and FAA certification affected by SB190-57-0005, the PART I of this bulletin must be accomplished before the aircraft logs 26.265 Flight Cycle(s) or 41.903 Flight Hour(s) after the accomplishment of SB190-57-0005, whichever occurs first. 2) According to the WFD regulation (§26.21), for aircraft under ANAC and FAA certification that have SB190-57-0005 modification factory-incorporated, the PART I of this bulletin must be accomplished before the aircraft logs 26.265 Flight Cycle(s) or 41.903 Flight Hour(s), whichever occurs first. (2) APPLICABLE TO PART II SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 3 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 4 Embraer recommends the accomplishment of PART II of this bulletin in the next 6,250 Flight Cycle(s) or 7,500 Flight Hour(s) from the first issue date of this bulletin, whichever occurs first. NOTE: 1) According to the WFD regulation (§26.21), for aircraft under ANAC and FAA certification affected by SB190-57-0005, the PART II of this bulletin must be accomplished before the aircraft logs 26.265 Flight Cycle(s) or 41.903 Flight Hour(s) after the accomplishment of SB190-57-0005, whichever occurs first. 2) According to the WFD regulation (§26.21), for aircraft under ANAC and FAA certification that have SB190-57-0005 modification factory-incorporated, the PART II of this bulletin must be accomplished before the aircraft logs 26.265 Flight Cycle(s) or 41.903 Flight Hour(s), whichever occurs first. (3) APPLICABLE TO PART III Embraer recommends the accomplishment of PART III of this bulletin in the next 6,250 Flight Cycle(s) or 7,500 Flight Hour(s) from the first issue date of this bulletin, whichever occurs first. NOTE: 1) According to the WFD regulation (§26.21), for aircraft under ANAC and FAA certification affected by SB190-57-0005, the PART III of this bulletin must be accomplished before the aircraft logs 26.265 Flight Cycle(s) or 41.903 Flight Hour(s) after the accomplishment of SB190-57-0005, whichever occurs first. 2) According to the WFD regulation (§26.21), for aircraft under ANAC and FAA certification that have SB190-57-0005 modification factory-incorporated, the PART III of this bulletin must be accomplished before the aircraft logs 26.265 Flight Cycle(s) or 41.903 Flight Hour(s), whichever occurs first. (4) APPLICABLE TO PART IV Embraer recommends the accomplishment of PART IV of this bulletin in the next 6,250 Flight Cycle(s) or 7,500 Flight Hour(s) from the first issue date of this bulletin, whichever occurs first. NOTE: 1) According to the WFD regulation (§26.21), for aircraft under ANAC and FAA certification affected by SB190-57-0005, the PART IV of this bulletin must be accomplished before the aircraft logs 26.265 Flight Cycle(s) or 41.903 Flight Hour(s) after the accomplishment of SB190-57-0005, whichever occurs first. 2) According to the WFD regulation (§26.21), for aircraft under ANAC and FAA certification that have SB190-57-0005 modification factory-incorporated, the PART IV of this bulletin must be accomplished before the aircraft logs 26.265 Flight Cycle(s) or 41.903 Flight Hour(s), whichever occurs first. NOTE: The indication RC (Required for Compliance) is presented in the accomplishment instructions and/or figures. If this service bulletin is mandated by an Airworthiness Directive (AD) that refers to any step identified as RC, it must be done to comply with the AD. If a step is indicated as "RC Exempt," then the RC requirement is removed from that step. Steps not identified with RC are recommended and may be deviated from, done as a part of other actions, or done with accepted methods different from those given in the SB provided that any RC step can still be done and the aircraft can be put back to a serviceable condition. An Alternative Method of Compliance (AMOC) is not necessary in case of deviations of the steps that are not identified as RC. SERVICE BULLETIN SB190-57-0056 Page 4 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 5 F. APPROVAL The changes to the type design specified in this Service Bulletin have been approved by Agência Nacional de Aviação Civil (ANAC). NOTE: If any aircraft listed in the SB effectivity has an incorporated modification or repair that is not from EMBRAER and which affects the content of this Service Bulletin, the operator will take full responsibility for obtaining approval by a regulatory agency for any adaptation necessary before the incorporation of this Service Bulletin. G. ESTIMATED MANPOWER This is an estimate of the manpower necessary to accomplish this Service Bulletin on a single aircraft. It is intended for direct labor only, performed by experienced personnel and does not include the time to plan, prepare or inspect the work. Sealant, paint or adhesive curing times are not included either. It is assumed that all the tools, parts and other means are readily available when necessary. An adjustment to these values may be necessary to meet particular circumstances. NOTE: These estimates do not include the time necessary to defuel the tanks. (1) APPLICABLE TO PART I – Access opening: 72.0 man-hours. – Inspection: 3.0 man-hours. – Modification: 392.0 man-hours. – Access closure: 96.0 man-hours. – Test: 6.0 man-hours. (2) APPLICABLE TO PART II – Access opening: 72.0 man-hours. – Inspection: 3.0 man-hours. – Modification: 320.0 man-hours. – Access closure: 96.0 man-hours. – Test: 6.0 man-hours. (3) APPLICABLE TO PART III – Access opening: 72.0 man-hours. – Inspection: 3.0 man-hours. – Modification: 392.0 man-hours. – Access closure: 96.0 man-hours. – Test: 6.0 man-hours. (4) APPLICABLE TO PART IV – Access opening: 72.0 man-hours. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 5 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 6 – Inspection: 3.0 man-hours. – Modification: 320.0 man-hours. – Access closure: 96.0 man-hours. – Test: 6.0 man-hours. H. WEIGHT AND BALANCE (1) APPLICABLE TO PART I – Change in basic weight: + 35.591 lb (+ 16.144 kg). – Change in basic moment: + 23,875.60 lb.in (+ 275.08 kg.m). (2) APPLICABLE TO PART II – Change in basic weight: + 12.692 lb (+ 5.757 kg). – Change in basic moment: + 9,083.98 lb.in (+ 104.66 kg.m). (3) APPLICABLE TO PART III – Change in basic weight: + 35.576 lb (+ 16.137 kg). – Change in basic moment: + 23,868.65 lb.in (+ 275.00 kg.m). (4) APPLICABLE TO PART IV – Change in basic weight: + 11.830 lb (+ 5.366 kg). – Change in basic moment: + 8,467.73 lb.in (+ 97.56 kg.m). I. SOFTWARE ACCOMPLISHMENT SUMMARY None. J. REFERENCES AMM 190/( ) Aircraft Maintenance Manual PART II - 06-44-00 - DIMENSIONS ANDAREAS. AMM 190/( ) Aircraft Maintenance Manual PART II - 07-10-01 - LIFTING & SHORING. AMM 190/( ) Aircraft Maintenance Manual PART II - 12-11-01 and 12-11-05 -SERVICING. AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00, 20-10-01, 20-10-03,20-10-13, and 20-13-21 - STANDARD PRACTICES-AIRFRAME. AMM 190/( ) Aircraft Maintenance Manual PART II - 26-21-13 - FIRE PROTECTION. AMM 190/( ) Aircraft Maintenance Manual PART II - 27-81-03 - FLIGHT CONTROLS. AMM 190/( ) Aircraft Maintenance Manual PART II - 28-11-00, 28-11-03, 28-21-19, and28-21-21 - FUEL. AMM 190/( ) Aircraft Maintenance Manual PART II - 29-11-11 - HYDRAULIC POWER. SERVICE BULLETIN SB190-57-0056 Page 6 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 7 AMM 190/( ) Aircraft Maintenance Manual PART II - 30-11-07 and 30-11-08 - ICE ANDRAIN PROTECTION. AMM 190/( ) Aircraft Maintenance Manual PART II - 36-11-04 and 36-21-02 -PNEUMATIC. AMM 190/( ) Aircraft Maintenance Manual PART II - 51-50-00 - STANDARD PRACTICESAND STRUCTURES. AMM 190/( ) Aircraft Maintenance Manual PART II - 54-50-21, 54-50-22, and 54-50-23 -NACELLES/PYLONS. AMM 190/( ) Aircraft Maintenance Manual PART II - 57-49-02 - WINGS. AMM 190/( ) Aircraft Maintenance Manual PART II - 71-00-01 - POWERPLANT. AMM 190/( ) Aircraft Maintenance Manual PART II - 78-30-01 - EXHAUST. ITEM 190/( ) Illustrated Tool and Equipment Manual. NDT 190/( ) Nondestructive Testing Manual - Part 1 - 51 - STANDARD PRACTICESAND STRUCTURES. SRM 190/( ) Structural Repair Manual Part II - 51-21-00, 51-21-01, 51-21-02, 51-21-04, 51-21-05, 51-21-07, 51-40-02, 51-40-06, 51-42-02, 51-43-03, and 51-43-04 - STANDARD PRACTICES AND STRUCTURES. K. OTHER PUBLICATIONS AFFECTED AIPC 190/( ) Aircraft Illustrated Parts Catalog - 54-50-00, 54-50-21, and 54-50-23 -NACELLES/PYLONS. SRMI 190/( ) Structural Repair Manual Part I - 57-10-00 and 57-10-01 - WINGS. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 7 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 8 2. MATERIAL INFORMATION A. MATERIAL - PRICE AND AVAILABILITY (1) MATERIAL AVAILABLE FROM EMBRAER The kits below and the parts to be procured mentioned in paragraph 2.C. MATERIAL NECESSARY FOR EACH AIRCRAFT required for the accomplishment of this bulletin will be available from Embraer at no charge to the operator. Embraer will receive the "no charge" orders during a period of 36 months after the first release date of this service bulletin. The estimated delivery date (EDD) will be provided by Embraer upon request. EDD will consider Embraer inventory availability and distribution strategy defined by Fleet Performance & Reliability team (fleet.performance@embraer.com.br). The distribution strategy sets a limited quantity of kits per airline per month. When ordering, specify SB 190-57-0056 and Top Kit PN presented in Table below, as applicable. RE F TOP KIT PN Unit Price (US$) TOP KIT EFFECTIVITY 01 BS1905700560001 119,150.83 Applicable to PART I 02 BS1905700560002 21,009.76 Applicable to PART II 03 BS1905700560003 119,276.86 Applicable to PART III 04 BS1905700560004 21,009.76 Applicable to PART IV 05 BS1905700560005[1] 381.70 Applicable to all PARTS [1] One Top Kit PN BS1905700560005 is valid to lower the LH and RH pylon once. If it is necessary to lower the LH and/or RH pylon one more time, another Top Kit should be requested. (2) MATERIAL AVAILABLE FROM OTHER VENDORS None. B. INDUSTRY SUPPORT INFORMATION None. C. MATERIAL NECESSARY FOR EACH AIRCRAFT When applicable, the use of alternative or similar parts is allowed, once it is approved by Embraer as indicated in the related Embraer Technical Publications or through a formal Embraer communication channel. The necessary expendable or consumable parts presented in the AMM Tasks mentioned in this bulletin can be acquired from the operator's inventories or ordered as spares. When necessary, additional information is presented as Notes in the respective Table. SERVICE BULLETIN SB190-57-0056 Page 8 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 9 For ordering information and Top Kit effectivity refer to section 2.A. MATERIAL - PRICE AND AVAILABILITY of this Bulletin. (1) TOP KITS AND KITS Kit Summary: Top Kit Composition (Kit PN / Quantity) Top Kit PN 191-35754-601 191-35905-601 191-35754-602 191-35905-602 191-32775-601 BS1905700560001 01 - - - - BS1905700560002 - 01 - - - BS1905700560003 - - 01 - - BS1905700560004 - - - 01 - BS1905700560005 - - - - 01 (a) Kit PN 191-35754-601 - LH FORWARD WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES 190-18665-021 DoublerReinforcement -0 1 0 1 2 190-18664-021 DoublerReinforcement -0 1 0 1 2 190-18663-021 DoublerReinforcement -0 1 0 1 2 190-33611-607 Fitting 190-33611-401 01 01 3 190-33611-403 190-33611-405 190-33611-421 190-33611-431 190-33615-603 Fitting 190-33615-401 01 01 3 190-33615-403 190-33615-405 190-33615-421 190-33615-431 190-33637-621 Fitting 190-33637-401 01 01 3 190-33637-622 Fitting 190-33637-402 01 01 3 HST154AP-10-14 Pin HST154AP-10-10 02 01 3 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 9 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 10 (a) (Continued) Kit PN 191-35754-601 - LH FORWARD WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES HST154AP-10-18 Pin HST154AP-10-14 03 02 3 HST154AP-10-20 Pin HST154AP-10-17 03 02 3 HST154AP-12-14 Pin HST154AP-12-10 02 01 3 HST154AP-12-18 Pin HST154AP-12-14 03 02 3 HST154AP-12-21 Pin HST154AP-12-17 02 01 3 HST154AP-12-26 Pin HST154AP-12-22 03 02 3 HST154AP-12-27 Pin HST154AP-12-23 02 01 3 HST154AP-12-30 Pin HST154AP-12-27 03 02 3 HST154AP-12-32 Pin HST154AP-12-29 04 03 3 HST154AP-14-28 Pin HST154AP-14-24 02 01 3 HST154AP-14-39 Pin HST154AP-14-36 05 04 3 HST154AP-14-42 Pin HST154AP-14-39 02 01 3 HST154AP-14-47 Pin HST154AP-14-44 02 01 3 HST154AP-16-34 Pin HST154AP-16-31 02 01 3 HST154AP-16-36 Pin HST154AP-16-33 02 01 3 HST154AP-16-42 Pin HST154AP-16-39 02 01 3 MS14181-06020LX Bolt MS14181-06016L 01 01 3 MS14181-06022LX Bolt MS14181-06018L 01 01 3 MS14181-07034LX Bolt MS14181-07030L 01 01 3 MS14181-07042LX Bolt MS14181-07038L 01 01 3 MS14181-07054LX Bolt MS14181-07050L 01 01 3 MS14181-09046LX Bolt MS14181-09042L 01 01 3 MS14181-12056LX Bolt MS14181-12052L 01 01 3 MS14182L06 Nut MS14182L06 02 02 7 MS14182L07 Nut MS14182L07 03 03 7 MS14182L09 Nut MS14182L09 01 01 7 MS14182L12 Nut MS14182L12 01 01 7 MS14183L-12 Washer MS14183L-12 01 01 7 MS14183L-6 Washer MS14183L-6 04 04 7 MS14183L-7 Washer MS14183L-7 06 06 7 MS14183L-9 Washer MS14183L-9 02 02 7 MS14183L-C12 Washer MS14183L-C12 01 01 7 MS14183L-C6 Washer MS14183L-C6 02 02 7 MS14183L-C7 Washer MS14183L-C7 03 03 7 MS14183L-C9 Washer MS14183L-C9 01 01 7 SERVICE BULLETIN SB190-57-0056 Page 10 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 11 (a) (Continued) Kit PN 191-35754-601 - LH FORWARD WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES NAS1149C0763R Washer NAS1149C0663R 01 01 3 NAS1726C5PE Nut NAS1726C5PE 06 06 7 NAS1726C6PE Nut NAS1726C6PE 12 12 7 NAS1726C7PE Nut NAS1726C7PE 07 07 7 NAS1726C8PE Nut NAS1726C8PE 04 04 7 HST10BJ-10-6 Pin - 07 06 2 HST10BJ-6-12 Pin - 57 50 2 HST10BJ-6-5 Pin - 09 07 2 HST10BJ-6-6 Pin - 18 15 2 HST10BJ-6-7 Pin - 43 38 2 HST10BJ-6-8 Pin - 95 86 2 HST10BJ-6-9 Pin - 18 16 2 HST10BJ-8-6 Pin - 54 48 2 HST79CK-10 Collar - 81 71 2 HST79CK-6 Collar - 230 212 2 HST79CK-8 Collar - 71 64 2 HST10BJ-10-12 Pin - 10 08 2 HST10BJ-10-13 Pin - 25 22 2 HST10BJ-10-16 Pin - 10 08 2 HST10BJ-10-17 Pin - 15 13 2 HST10BJ-10-18 Pin - 16 14 2 HST10BJ-8-12 Pin HST10BJ-8-10 05 04 3 HST10BJ-8-16 Pin - 02 01 2 HST10BJ-8-20 Pin - 06 05 2 HST10BJ-8-23 Pin - 07 06 2 HST154AP-10-36 Pin HST154AP-10-32 02 01 3 HST154AP-16-47 Pin HST154AP-16-44 02 01 3 CCR244SS-3-3 Rivet - 10 08 2 MS21059L3 Nut Plate - 04 04 2 HST110BJ-10-12 Pin HST11BJ-10-10 08 06 3 HST110BJ-10-16 Pin HST11BJ-10-14 06 04 3 171-00365-001 Shim - 02 02 2 HST84CK-10 Collar - 14 10 2 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 11 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 12 (b) Kit PN 191-35905-601 - LH REAR WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES 190-18668-021 DoublerReinforcement -0 1 0 1 2 190-18667-021 DoublerReinforcement -0 1 0 1 2 190-18666-021 DoublerReinforcement -0 1 0 1 2 190-33621-601 Fitting 190-33621-401 01 01 3190-33621-421 190-33633-603 Fitting 190-33633-403 01 01 3190-33633-405 190-33633-421 190-33643-605 Fitting 190-33643-403 01 01 3190-33643-405 190-33643-421 190-33635-621 Fitting 190-33635-401 01 01 3190-33635-421 190-33645-601 Fitting 190-33645-401 01 01 3190-33645-421 HST154AP-12-26 Pin HST154AP-12-22 14 12 3 HST154AP-12-27 Pin HST154AP-12-27 03 02 3 HST154AP-14-31 Pin HST154AP-14-27 03 02 3 HST154AP-14-35 Pin HST154AP-14-31 03 02 3 NAS1149C0763R Washer NAS1149C0663R 04 04 3 NAS1726C6PE Nut NAS1726C6PE 14 14 7 NAS1726C7PE Nut NAS1726C7PE 04 04 7 HST10BJ-10-7 Pin - 07 06 2 HST10BJ-10-9 Pin - 07 06 2 HST10BJ-6-10 Pin - 18 16 2 HST10BJ-6-11 Pin - 40 36 2 HST10BJ-6-5 Pin - 12 10 2 HST10BJ-6-6 Pin - 56 51 2 HST10BJ-6-7 Pin - 14 12 2 HST10BJ-6-8 Pin - 51 46 2 HST10BJ-6-9 Pin - 16 14 2 HST10BJ-8-5 Pin - 21 19 2 HST10BJ-8-6 Pin - 21 19 2 HST79CK-10 Collar - 77 69 2 SERVICE BULLETIN SB190-57-0056 Page 12 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 13 (b) (Continued) Kit PN 191-35905-601 - LH REAR WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES HST79CK-6 Collar - 222 185 2 HST79CK-8 Collar - 85 78 2 HST10BJ-10-12 Pin - 11 10 2 HST10BJ-10-13 Pin - 07 06 2 HST10BJ-10-14 Pin - 09 08 2 HST10BJ-10-16 Pin - 03 01 2 HST10BJ-10-17 Pin - 11 10 2 HST10BJ-10-20 Pin - 24 22 2 HST10BJ-8-11 Pin - 07 06 2 HST10BJ-8-12 Pin HST10BJ-8-9 03 02 3 HST10BJ-8-13 Pin - 16 14 2 HST10BJ-8-14 Pin HST10BJ-8-12 03 02 3 HST10BJ-8-16 Pin HST10BJ-8-13 05 04 3 HST10BJ-8-9 Pin - 14 12 2 CCR244SS-3-3 Rivet - 10 08 2 MS21059L3 Nut Plate - 04 04 2 HST110BJ-10-11 Pin HST11BJ-10-10 10 08 3 HST110BJ-10-16 Pin HST11BJ-10-14 05 03 3 HST110BJ-10-20 Pin HST11BJ-10-18 04 02 3 171-00365-003 Shim - 01 01 2 HST84CK-10 Collar - 19 13 2 (c) Kit PN 191-35754-602 - RH FORWARD WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES 190-18665-022 DoublerReinforcement -0 1 0 1 2 190-18664-022 DoublerReinforcement -0 1 0 1 2 190-18663-022 DoublerReinforcement -0 1 0 1 2 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 13 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 14 (c) (Continued) Kit PN 191-35754-602 - RH FORWARD WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES 190-33611-608 Fitting 190-33611-402 01 01 3 190-33611-404 190-33611-406 190-33611-422 190-33611-432 190-33615-604 Fitting 190-33615-402 01 01 3 190-33615-404 190-33615-406 190-33615-422 190-33615-432 190-33637-621 Fitting 190-33637-401 01 01 3 190-33637-622 Fitting 190-33637-402 01 01 3 HST154AP-10-14 Pin HST154AP-10-10 02 01 3 HST154AP-10-18 Pin HST154AP-10-14 03 02 3 HST154AP-10-20 Pin HST154AP-10-17 03 02 3 HST154AP-12-14 Pin HST154AP-12-10 02 01 3 HST154AP-12-18 Pin HST154AP-12-14 03 02 3 HST154AP-12-21 Pin HST154AP-12-17 02 01 3 HST154AP-12-26 Pin HST154AP-12-22 03 02 3 HST154AP-12-27 Pin HST154AP-12-23 02 01 3 HST154AP-12-30 Pin HST154AP-12-27 03 02 3 HST154AP-12-32 Pin HST154AP-12-29 04 03 3 HST154AP-14-28 Pin HST154AP-14-24 02 01 3 HST154AP-14-39 Pin HST154AP-14-36 05 04 3 HST154AP-14-42 Pin HST154AP-14-39 02 01 3 HST154AP-14-47 Pin HST154AP-14-44 02 01 3 HST154AP-16-34 Pin HST154AP-16-31 02 01 3 HST154AP-16-36 Pin HST154AP-16-33 02 01 3 HST154AP-16-42 Pin HST154AP-16-39 02 01 3 MS14181-06020LX Bolt MS14181-06016L 01 01 3 MS14181-06022LX Bolt MS14181-06018L 01 01 3 MS14181-07034LX Bolt MS14181-07030L 01 01 3 MS14181-07042LX Bolt MS14181-07038L 01 01 3 MS14181-07054LX Bolt MS14181-07050L 01 01 3 MS14181-09046LX Bolt MS14181-09042L 01 01 3 SERVICE BULLETIN SB190-57-0056 Page 14 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 15 (c) (Continued) Kit PN 191-35754-602 - RH FORWARD WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES MS14181-12056LX Bolt MS14181-12052L 01 01 3 MS14182L06 Nut MS14182L06 02 02 7 MS14182L07 Nut MS14182L07 03 03 7 MS14182L09 Nut MS14182L09 01 01 7 MS14182L12 Nut MS14182L12 01 01 7 MS14183L-12 Washer MS14183L-12 01 01 7 MS14183L-6 Washer MS14183L-6 04 04 7 MS14183L-7 Washer MS14183L-7 06 06 7 MS14183L-9 Washer MS14183L-9 02 02 7 MS14183L-C12 Washer MS14183L-C12 01 01 7 MS14183L-C6 Washer MS14183L-C6 02 02 7 MS14183L-C7 Washer MS14183L-C7 03 03 7 MS14183L-C9 Washer MS14183L-C9 01 01 7 NAS1149C0763R Washer NAS1149C0663R 01 01 3 NAS1726C5PE Nut NAS1726C5PE 06 06 7 NAS1726C6PE Nut NAS1726C6PE 12 12 7 NAS1726C7PE Nut NAS1726C7PE 07 07 7 NAS1726C8PE Nut NAS1726C8PE 04 04 7 HST10BJ-10-6 Pin - 07 06 2 HST10BJ-6-12 Pin - 57 50 2 HST10BJ-6-5 Pin - 09 07 2 HST10BJ-6-6 Pin - 18 15 2 HST10BJ-6-7 Pin - 43 38 2 HST10BJ-6-8 Pin - 95 86 2 HST10BJ-6-9 Pin - 18 16 2 HST10BJ-8-6 Pin - 54 48 2 HST79CK-10 Collar - 81 71 2 HST79CK-6 Collar - 230 212 2 HST79CK-8 Collar - 71 64 2 HST10BJ-10-12 Pin - 10 08 2 HST10BJ-10-13 Pin - 25 22 2 HST10BJ-10-16 Pin - 10 08 2 HST10BJ-10-17 Pin - 15 13 2 HST10BJ-10-18 Pin - 16 14 2 HST10BJ-8-12 Pin HST10BJ-8-10 05 04 3 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 15 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 16 (c) (Continued) Kit PN 191-35754-602 - RH FORWARD WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES HST10BJ-8-16 Pin - 02 01 2 HST10BJ-8-20 Pin - 06 05 2 HST10BJ-8-23 Pin - 07 06 2 HST154AP-10-36 Pin HST154AP-10-32 02 01 3 HST154AP-16-47 Pin HST154AP-16-44 02 01 3 CCR244SS-3-3 Rivet - 10 08 2 MS21059L3 Nut Plate - 04 04 2 HST110BJ-10-12 Pin HST11BJ-10-10 08 06 3 HST110BJ-10-16 Pin HST11BJ-10-14 06 04 3 171-00365-001 Shim - 02 02 2 HST84CK-10 Collar - 14 10 2 (d) Kit PN 191-35905-602 - RH REAR WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES 190-18668-022 DoublerReinforcement -0 1 0 1 2 190-18667-022 DoublerReinforcement -0 1 0 1 2 190-18666-022 DoublerReinforcement -0 1 0 1 2 190-33621-602 Fitting 190-33621-402 01 01 3190-33621-422 190-33633-604 Fitting 190-33633-404 01 01 3190-33633-406 190-33633-422 190-33643-606 Fitting 190-33643-404 01 01 3190-33643-406 190-33643-422 190-33635-622 Fitting 190-33635-402 01 01 3190-33635-422 190-33645-602 Fitting 190-33645-402 01 01 3190-33645-422 HST154AP-12-26 Pin HST154AP-12-22 14 12 3 HST154AP-12-27 Pin HST154AP-12-27 03 02 3 SERVICE BULLETIN SB190-57-0056 Page 16 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 17 (d) (Continued) Kit PN 191-35905-602 - RH REAR WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES HST154AP-14-31 Pin HST154AP-14-27 03 02 3 HST154AP-14-35 Pin HST154AP-14-31 03 02 3 NAS1149C0763R Washer NAS1149C0663R 04 04 3 NAS1726C6PE Nut NAS1726C6PE 14 14 7 NAS1726C7PE Nut NAS1726C7PE 04 04 7 HST10BJ-10-7 Pin - 07 06 2 HST10BJ-10-9 Pin - 07 06 2 HST10BJ-6-10 Pin - 18 16 2 HST10BJ-6-11 Pin - 40 36 2 HST10BJ-6-5 Pin - 12 10 2 HST10BJ-6-6 Pin - 56 51 2 HST10BJ-6-7 Pin - 14 12 2 HST10BJ-6-8 Pin - 51 46 2 HST10BJ-6-9 Pin - 16 14 2 HST10BJ-8-5 Pin - 21 19 2 HST10BJ-8-6 Pin - 21 19 2 HST79CK-10 Collar - 77 69 2 HST79CK-6 Collar - 222 185 2 HST79CK-8 Collar - 85 78 2 HST10BJ-10-12 Pin - 11 10 2 HST10BJ-10-13 Pin - 07 06 2 HST10BJ-10-14 Pin - 09 08 2 HST10BJ-10-16 Pin - 03 01 2 HST10BJ-10-17 Pin - 11 10 2 HST10BJ-10-20 Pin - 24 22 2 HST10BJ-8-11 Pin - 07 06 2 HST10BJ-8-12 Pin HST10BJ-8-9 03 02 3 HST10BJ-8-13 Pin - 16 14 2 HST10BJ-8-14 Pin HST10BJ-8-12 03 02 3 HST10BJ-8-16 Pin HST10BJ-8-13 05 04 3 HST10BJ-8-9 Pin - 14 12 2 CCR244SS-3-3 Rivet - 10 08 2 MS21059L3 Nut Plate - 04 04 2 HST110BJ-10-11 Pin HST11BJ-10-10 10 08 3 HST110BJ-10-16 Pin HST11BJ-10-14 05 03 3 HST110BJ-10-20 Pin HST11BJ-10-18 04 02 3 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 17 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 18 (d) (Continued) Kit PN 191-35905-602 - RH REAR WING LOWER SKIN PANEL - REINFORCEMENT NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES 171-00365-003 Shim - 01 01 2 HST84CK-10 Collar - 19 13 2 (e) Kit PN 191-32775-601 - HYDRAULIC TUBES REWORK (LH and RH Sides) NEW PN DESCRIPTION OLD PN QTYSUP QTYRQD DISP/NOTES D10036-06 Permaswage Union - 02 02 2 D10036-08 Permaswage Union - 03 03 2 D10036-10 Permaswage Union - 02 02 2 (2) MATERIAL TO BE PROCURED (a) Parts 1) If necessary, the oversize pins below should be procured from the operator’s inventories or ordered as spares from Embraer. Applicable to PART I and PART III NEW PN DESCRIPTION OLD PN QTY DISP/Notes HST254AP-10-14 Pin (oversize PNHST154AP-10-14) -A R 6 192-00101-001 Pin (oversize PNHST154AP-10-18) -A R 6 HST254AP-10-20 Pin (oversize PNHST154AP-10-20) -A R 6 HST254AP-12-14 Pin (oversize PNHST154AP-12-14) -A R 6 192-00102-001 Pin (oversize PNHST154AP-12-18) -A R 6 HST254AP-12-21 Pin (oversize PNHST154AP-12-21) -A R 6 HST254AP-12-26 Pin (oversize PNHST154AP-12-26) -A R 6 HST254AP-12-27 Pin (oversize PNHST154AP-12-27) -A R 6 HST254AP-12-30 Pin (oversize PNHST154AP-12-30) -A R 6 HST254AP-12-32 Pin (oversize PNHST154AP-12-32) -A R 6 SERVICE BULLETIN SB190-57-0056 Page 18 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 19 (Continued) Applicable to PART I and PART III NEW PN DESCRIPTION OLD PN QTY DISP/Notes 192-00103-001 Pin (oversize PNHST154AP-14-28) -A R 6 HST254AP-14-39 Pin (oversize PNHST154AP-14-39) -A R 6 192-00104-001 Pin (oversize PNHST154AP-14-42) -A R 6 HST254AP-14-47 Pin (oversize PNHST154AP-14-47) -A R 6 192-00105-001 Pin (oversize PNHST154AP-16-34) -A R 6 192-00106-001 Pin (oversize PNHST154AP-16-36) -A R 6 HST254AP-16-42 Pin (oversize PNHST154AP-16-42) -A R 6 MS14181-06020LY Bolt (oversize PNMS14181-06020LX) -A R 6 MS14181-06022LY Bolt (oversize PNMS14181-06022LX) -A R 6 MS14181-07034LY Bolt (oversize PNMS14181-07034LX) -A R 6 MS14181-07042LY Bolt (oversize PNMS14181-07042LX) -A R 6 MS14181-07054LY Bolt (oversize PNMS14181-07054LX) -A R 6 MS14181-09046LY Bolt (oversize PNMS14181-09046LX) -A R 6 MS14181-12056LY Bolt (oversize PNMS14181-12056LX) -A R 6 HST110BJ-10-6 Pin (oversize PNHST10BJ-10-6) -A R 6 HST110BJ-6-12 Pin (oversize PNHST10BJ-6-12) -A R 6 HST110BJ-6-5 Pin (oversize PNHST10BJ-6-5) -A R 6 HST110BJ-6-6 Pin (oversize PNHST10BJ-6-6) -A R 6 HST110BJ-6-7 Pin (oversize PNHST10BJ-6-7) -A R 6 HST110BJ-6-8 Pin (oversize PNHST10BJ-6-8) -A R 6 HST110BJ-6-9 Pin (oversize PNHST10BJ-6-9) -A R 6 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 19 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 20 (Continued) Applicable to PART I and PART III NEW PN DESCRIPTION OLD PN QTY DISP/Notes HST110BJ-8-6 Pin (oversize PNHST10BJ-8-6) -A R 6 HST110BJ-10-12 Pin (oversize PNHST10BJ-10-12) -A R 6 HST110BJ-10-13 Pin (oversize PNHST10BJ-10-13) -A R 6 HST110BJ-10-16 Pin (oversize PNHST10BJ-10-16) -A R 6 HST110BJ-10-17 Pin (oversize PNHST10BJ-10-17) -A R 6 HST110BJ-10-18 Pin (oversize PNHST10BJ-10-18) -A R 6 HST110BJ-8-12 Pin (oversize PNHST10BJ-8-12) -A R 6 HST110BJ-8-16 Pin (oversize PNHST10BJ-8-16) -A R 6 HST110BJ-8-20 Pin (oversize PNHST10BJ-8-20) -A R 6 HST110BJ-8-23 Pin (oversize PNHST10BJ-8-23) -A R 6 HST254AP-10-36 Pin (oversize PNHST154AP-10-36) -A R 6 192-00107-001 Pin (oversize PNHST154AP-16-47) -A R 6 HST410BJ-10-16 Pin (oversize PNHST110BJ-10-16) -A R 6 HST410BJ-10-12 Pin (oversize PNHST110BJ-10-12) -A R 6 HST84CK-6 Collar (oversize PNHST79CK-6) -A R 6 HST84CK-8 Collar (oversize PNHST79CK-8) -A R 6 HST84CK-10 Collar (oversize PNHST79CK-10) -A R 6 Applicable to PART II and PART IV NEW PN DESCRIPTION OLD PN QTY DISP/Notes HST410BJ-10-16 Pin (oversize PNHST110BJ-10-16) -A R 6 HST410BJ-10-11 Pin (oversize PNHST110BJ-10-11) -A R 6 SERVICE BULLETIN SB190-57-0056 Page 20 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 21 (Continued) Applicable to PART II and PART IV NEW PN DESCRIPTION OLD PN QTY DISP/Notes HST410BJ-10-20 Pin (oversize PNHST110BJ-10-20) -A R 6 HST254AP-12-26 Pin (oversize PNHST154AP-12-26) -A R 6 HST254AP-12-27 Pin (oversize PNHST154AP-12-27) -A R 6 HST254AP-14-31 Pin (oversize PNHST154AP-14-31) -A R 6 HST254AP-14-35 Pin (oversize PNHST154AP-14-35) -A R 6 HST110BJ-10-7 Pin (oversize PNHST10BJ-10-7) -A R 6 HST110BJ-10-9 Pin (oversize PNHST10BJ-10-9) -A R 6 HST110BJ-6-10 Pin (oversize PNHST10BJ-6-10) -A R 6 HST110BJ-6-11 Pin (oversize PNHST10BJ-6-11) -A R 6 HST110BJ-6-5 Pin (oversize PNHST10BJ-6-5) -A R 6 HST110BJ-6-6 Pin (oversize PNHST10BJ-6-6) -A R 6 HST110BJ-6-7 Pin (oversize PNHST10BJ-6-7) -A R 6 HST110BJ-6-8 Pin (oversize PNHST10BJ-6-8) -A R 6 HST110BJ-6-9 Pin (oversize PNHST10BJ-6-9) -A R 6 HST110BJ-8-5 Pin (oversize PNHST10BJ-8-5) -A R 6 HST110BJ-8-6 Pin (oversize PNHST10BJ-8-6) -A R 6 HST110BJ-10-11 Pin (oversize PNHST10BJ-10-11) -A R 6 HST110BJ-10-12 Pin (oversize PNHST10BJ-10-12) -A R 6 HST110BJ-10-13 Pin (oversize PNHST10BJ-10-13) -A R 6 HST110BJ-10-14 Pin (oversize PNHST10BJ-10-14) -A R 6 HST110BJ-10-16 Pin (oversize PNHST10BJ-10-16) -A R 6 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 21 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 22 (Continued) Applicable to PART II and PART IV NEW PN DESCRIPTION OLD PN QTY DISP/Notes HST110BJ-10-17 Pin (oversize PNHST10BJ-10-17) -A R 6 HST110BJ-10-20 Pin (oversize PNHST10BJ-10-20) -A R 6 HST110BJ-8-11 Pin (oversize PNHST10BJ-8-11) -A R 6 HST110BJ-8-12 Pin (oversize PNHST10BJ-8-12) -A R 6 HST110BJ-8-13 Pin (oversize PNHST10BJ-8-13) -A R 6 HST110BJ-8-14 Pin (oversize PNHST10BJ-8-14) -A R 6 HST110BJ-8-16 Pin (oversize PNHST10BJ-8-16) -A R 6 HST110BJ-8-9 Pin (oversize PNHST10BJ-8-9) -A R 6 HST84CK-6 Collar (oversize PNHST79CK-6) -A R 6 HST84CK-8 Collar (oversize PNHST79CK-8) -A R 6 HST84CK-10 Collar (oversize PNHST79CK-10) -A R 6 2) If necessary, the second oversize of the recommended pins/bolts should be procured from the operator’s inventories or from a local supplier. 3) If necessary, the parts below should be procured from the operator’s inventories, or from a local supplier, or ordered as spares from Embraer. Applicable to all Parts NEW PN DESCRIPTION OLD PN QTY DISP/Notes PE22072L14 Castellated Nut PE22072L14 AR 6 / [1] MS24665-372 Cotter Pin MS24665-372 AR 7 / [2] MS24665-374 Cotter Pin MS24665-374 AR 7 / [2] MS24665-376 Cotter Pin MS24665-376 AR 7 / [2] [1] The castellated nut PN PE22072L14 should be replaced with a new one if it is out of the drag torque range of 7.91 to 67.79 N.m (70 to 600 lb.in). Refer to Figure 4. [2] Applicable to aircraft with the lock washer, L-profile and internal shear pin with greater head installed. Refer to Figure 4. (b) Consumable Materials The material below or equivalent required for the accomplishment of this bulletin should be procured from the operator’s inventories or from a local supplier. SERVICE BULLETIN SB190-57-0056 Page 22 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 23 Applicable to all PARTS NEW PN DESCRIPTION OLD PN QTY DISP/Notes NAFTOSEAL MC 780 C-2 Sealant - AR 6/ [1] 2007B1/2ME654SK Sealant - AR 6/ [2] ARDROX AV-15 Corrosion InhibitingCompound -A R 6 / [3] F-925 Torque Seal - AR 6/ [4] COR-BAN 27L Corrosion InhibitingCompound -A R 6 / [5] [1] Polysulfide Interfaying Sealant Type IV Cl 2 (MEP_09-084) NAFTOSEAL MC 780 C-2 [2] Polysulfide Fuel Tank Sealant (MEP_09-084) 2007B1/2ME654SK [3] Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15. [4] Yellow Torque Seal (MEP 09-068) F-925. [5] Corrosion Inhibiting Compound (MEP_09-075) COR-BAN 27L. DISPOSITION: 2 = Incorporate part bearing NEW PN 3 = Replace part bearing OLD PN with part bearing NEW PN 6 = Apply as required 7 = Replace with part bearing same PN QUANTITY: AR = As Required (c) Kit Updating None. D. MATERIAL NECESSARY FOR EACH SPARE None. E. REIDENTIFIED PARTS The information necessary to modify and/or reidentify the parts, when necessary, is presented in the referenced Notes. DESCRIPTION OLD PN NEW PN Notes Fairing Instl, MVBL and Aft LH Pylon 190-11302-503 190-11302-603 [1] Fairing Instl, MVBL and Aft LH Pylon 190-11302-507 190-11302-607 [1] Fairing Instl, MVBL and Aft LH Pylon 190-11302-509 190-11302-609 [1] Fairing Instl, MVBL and Aft LH Pylon 190-11302-511 190-11302-611 [1] Fairing Instl, MVBL and Aft LH Pylon 190-11302-519 190-11302-619 [1] [1] For specific instructions on how to proceed with this identification, refer to 3. ACCOMPLISHMENT INSTRUCTIONS. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 23 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 24 (Continued) DESCRIPTION OLD PN NEW PN Notes Fairing Instl, MVBL and Aft RH Pylon 190-11303-503 190-11303-603 [1] Fairing Instl, MVBL and Aft RH Pylon 190-11303-507 190-11303-607 [1] Fairing Instl, MVBL and Aft RH Pylon 190-11303-509 190-11303-609 [1] Fairing Instl, MVBL and Aft RH Pylon 190-11303-511 190-11303-611 [1] Fairing Instl, MVBL and Aft RH Pylon 190-11303-521 190-11303-621 [1] Skin 5 Assy-Lateral Fairing, Pylon 190-03450-403 190-03450-603 [1] Skin 5 Assy-Lateral Fairing, Pylon 190-03450-404 190-03450-604 [1] Skin 5 Assy-Lateral Fairing, Pylon 190-03450-405 190-03450-605 [1] Skin 5 Assy-Lateral Fairing, Pylon 190-03450-406 190-03450-606 [1] Skin 5 Assy-Lateral Fairing, Pylon 190-03450-407 190-03450-607 [1] Skin 5 Assy-Lateral Fairing, Pylon 190-03450-408 190-03450-608 [1] Skin 5 Assy-Lateral Fairing, Pylon 190-03450-409 190-03450-609 [1] Skin 5 Assy-Lateral Fairing, Pylon 190-03450-410 190-03450-610 [1] Skin 6 Assy-Lateral Fairing, Pylon 190-03249-403 190-03249-603 [1] Skin 6 Assy-Lateral Fairing, Pylon 190-03249-404 190-03249-604 [1] Skin 6 Assy-Lateral Fairing, Pylon 190-03249-407 190-03249-607 [1] Skin 6 Assy-Lateral Fairing, Pylon 190-03249-408 190-03249-608 [1] Skin 6 Assy-Lateral Fairing, Pylon 190-03249-409 190-03249-609 [1] Skin 6 Assy-Lateral Fairing, Pylon 190-03249-410 190-03249-610 [1] [1] For specific instructions on how to proceed with this identification, refer to 3. ACCOMPLISHMENT INSTRUCTIONS. F. TOOLING - PRICE AND AVAILABILITY (1) FTI Kit FTI-190-57-0056 which specifies the required tooling and procedures on this Service Bulletin for the cold expansion, should be procured directly from the manufacturer Fatigue Technology Incorporated (FTI) at the address that follows, or from equivalent manufacturer. SERVICE BULLETIN SB190-57-0056 Page 24 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 25 FATIGUE TECHNOLOGY INC. 401 Andover Park East Seattle, Washington 98188-7605 USA Phone: 206.246.2010 www.fatiguetech.com FTI has designated the following tool kit numbers for this bulletin that may be purchased as follows: – Entire tool kit: kit number FTI-190-57-0056 – Durable tooling kit: Kit number DK-190-57-0056-1 (Diameter Number 6-0-N / 8-0-N / 10-0-N / 10-1-N) – Expendable tooling kit: Kit number EK-190-57-0056-1 (Diameter Number 6-0-N / 8-0-N / 10-0-N / 10-1-N) – Order individual components NOTE: The kits are purposefully designed this way so that an operator can order exactly what is necessary to do the repair, taking into consideration what each operator has in the tooling inventory. (2) The tooling below is required to lower and lift the pylon during the accomplishment of this bulletin. ITEM PN DESCRIPTION QTY Notes GSE 459 Tripod Assy 02 - GSE 115 Bootstrap Hoist Set - Engine 01 - - Tripod Jack, 0.5 Tons (Minimum) 02 [1] [1] Commercially available tripod jack with working capacity of 0.5 Tons, with 3 safety factor, namely 1.5 Tons. (3) The tooling presented below, required for the accomplishment of this bulletin, will be provided by Embraer upon request. Companies interested on renting it shall contact Embraer Special Programs (email special.programs@embraer.com.br) for the contractual arrangements, including commercial condition information. Companies interested on purchasing it shall contact Embraer Order Desk for orders and commercial condition information. As there is a limited quantity of this tooling available, the estimated delivery date (EDD) for purchasing or renting will consider Embraer inventory availability and distribution strategy defined by Fleet Performance & Reliability team (fleet.performance@embraer.com.br). TOOLING PN DESCRIPTION QTY Notes 191-35754-601-20C1 Fittings Alignment Tooling 01 [1] 191-35754-602-20C1 Fittings Alignment Tooling 01 [2] [1] Applicable to PART I and PART II [2] Applicable to PART III and PART IV (4) 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: Dec 05, 2019 Revision No.: SB190-57-0056 Page 25 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 26 3. ACCOMPLISHMENT INSTRUCTIONS NOTE: 1) For the purpose of this Service Bulletin, a Special Detailed Inspection (SDI) is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure or irregularity. The examination is likely to make extensive use of specialized Inspection Techniques and/or equipment. Intricate cleaning and substantial access or disassembly procedure may be required.” 2) Obey all of the WARNINGS and CAUTIONS included in the mentioned manuals and procedures. 3) The indication RC (Required for Compliance) is presented in the accomplishment instructions and/or figures. If this service bulletin is mandated by an Airworthiness Directive (AD) that refers to any step identified as RC, it must be done to comply with the AD. If a step is indicated as "RC Exempt," then the RC requirement is removed from that step. Steps not identified with RC are recommended and may be deviated from, done as a part of other actions, or done with accepted methods different from those given in the SB provided that any RC step can still be done and the aircraft can be put back to a serviceable condition. An Alternative Method of Compliance (AMOC) is not necessary in case of deviations of the steps that are not identified as RC. 4) These work instructions refer to methods, techniques, and practices described in other Embraer documents. When the words "refer to" are used and there are other acceptable methods, techniques, and practices (including tools, equipment, and test equipment), those acceptable methods, techniques, practices (including tools, equipment, and test equipment) may be used to complete the work. When the words "in accordance with" are included in the instruction, the methods, techniques, and practices specified (including tools, equipment, and test equipment) in the Embraer document must be used. 5) The Manuals and other documents are mentioned as acronyms or with a simplified form. Refer to section 1.J. REFERENCES for a more complete definition. 6) This Service Bulletin effectivity is divided into 04 PARTS. The SB PARTS division allows their independent accomplishment. REFERENCE APPLICATION TABLE SB PART APPLICABLE FIGURES I 1, 2, 3, 4, 5, 7, 8, 9, and 10 II 1, 2, 3, 4, 6, 7, 8, 9, and 10 III 1, 2, 3, 4, 5, 7, 8, 9, and 10 IV 1, 2, 3, 4, 6, 7, 8, 9, and 10 The steps below outline the general accomplishment instructions. The detailed sequence is included in the respective figure, when necessary. WARNING: MAKE SURE THAT THE AIRCRAFT IS IN A SAFE CONDITION BEFORE YOU ACCOMPLISH THE INSTRUCTIONS DESCRIBED IN THIS SERVICE BULLETIN. THIS IS TO PREVENT INJURY TO PERSONS AND/OR DAMAGE TO THE EQUIPMENT. 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. Defuel the aircraft fuel tanks. Refer to AMM TASK 12-11-01-650-802-A/300 - Fuel Tank - Pressure Defueling. SERVICE BULLETIN SB190-57-0056 Page 26 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 27 C. Drain the remaining fuel. Refer to AMM TASK 12-11-05-680-802-A/300 - Fuel Tank - Remaining Fuel Draining. D. Lift the aircraft on jacks. Refer to AMM TASK 07-10-01-500-801-A/200 - Complete Aircraft Jacking - Maintenance Practices. NOTE: Complete jacking is not required; lift up the aircraft just enough to alleviate the weight on wheels. E. APPLICABLE TO PART I AND PART II (1) Remove the access panel 521EB. Refer to AMM TASK 06-44-00-800-801-A/100 - Wing Access Doors and Panels and AMM TASK 28-11-03-000-801-A/400 - Fuel Tank Access Panel - Removal. (2) Remove and keep the items that follows to get access to the work area: (a) The LH pylon forward fairings. Refer to AMM TASK 54-50-21-000-801-A/400 - Pylon Forward Fairings - Removal. (b) The LH pylon side fairings. Refer to AMM TASK 54-50-22-000-801-A/400 - Pylon Side Fairings - Removal. (c) The LH pylon aft fairings. Refer to AMM TASK 54-50-23-000-801-B/400 - Pylon Aft Fairings - Removal. (d) The LH thrust reverser. Refer to AMM TASK 78-30-01-000-801-A/400 - Thrust Reverser - Removal. (e) The LH engine. Refer to AMM TASK 71-00-01-000-801-B/400 - Powerplant - Removal. (f) The LH slat torque tube (S7). Refer to AMM TASK 27-81-03-000-801-A/400 - Slat Torque Tube - Removal. (g) The applicable LH wing anti-ice ducts. Refer to AMM TASK 30-11-07-000-801-A/400 - Wing Anti-Ice Ducts - Removal. (h) The applicable fairings of the LH wing leading edge. Refer to AMM TASK 57-49-02-000-802-A/400 - Slat Track Cover - Removal. (i) The applicable support blocks of the hydraulic tubes. Refer to AMM TASK 20-10-03-000-801-A/400 - Tubing - Removal. NOTE: With a commercially available tape or equivalent component, do the protection of the existing tubes installed in the area near the lower link fuse pins. Do it to prevent damage on the tubes during the rework. (3) Release, as necessary, the items that follow, installed near and/or at the pylon area, to get access to the work area: NOTE: 1) If you completely remove any item with its parts from the aircraft, make sure that you mark its initial position of assembly before removal. Do it to prevent the wrong installation after the rework. 2) With protective cap/plug, plastic bags or equivalent component, do the protection of the applicable ducts and tubes to prevent leak splash and/or their contamination. (a) The screws and clamps of the applicable electrical harness. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 27 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 28 NOTE: Be careful when you handle the electrical harnesses and make sure that they are in a safe condition during the accomplishment of this bulletin. (b) The screws and clamps of the applicable fuel and hydraulic tubes. (c) The clamp shell that connects the tube of the engine fire extinguishing system to the drain valve. Refer to AMM TASK 20-10-13-000-801-A/400 - Clamp Shell (Typical) - Removal and to AMM TASK 26-21-13-000-801-A/400 - Engine Fire Extinguishing System Drain Valve Assembly - Removal. (d) The existing bonding jumpers of the LH pylon. Refer to AMM TASK 20-13-21-210-801- A/200 - Electrical Bonding Map - Standard Procedure and to SRM PART II 51-21-07 - SEALING REMOVAL. (e) If applicable, the existing bonding jumpers installed on the tubes. (f) The screws, clip mountings and electrical connectors of the applicable element sensor of the anti-icing and bleed leak detectors. Refer to AMM TASK 30-11-08-000-801-A/400 - Anti-Icing Leak Detectors - Removal and AMM TASK 36-21-02-000-801-A/400 - LH/RH Bleed Leak Detectors - Removal. NOTE: Be careful when you handle the element sensor not to damage them during the accomplishment of this bulletin. (g) The applicable bleed duct. Refer to AMM TASK 36-11-04-000-801-A/400 - Engine Bleed Lines - Removal. (h) The clamp shell of the fuel feed line. Refer to AMM TASK 20-10-13-000-801-A/400 - Clamp Shell (Typical) - Removal and to AMM TASK 28-21-21-000-802-A/400 - Fuel Feed Line (Pylon) - Removal. (i) The clamp shell of the motive-flow supply line. Refer to AMM TASK 28-21-19-000-802- A/400 - Motive-Flow Supply Line (Pylon) - Removal. (j) The applicable screws and clamps that attach the tube of the motive-flow supply line to the pylon structure. NOTE: Do it to get access to remove the existing bolt that attaches the LH pylon upper link outboard rod assy to the LH pylon. (k) Disconnect the existing tube from the firewall hydraulic shutoff valve and cut the applicable hydraulic tubes of the LH side. Refer to Figure 1. (l) Release the applicable supports assemblies of the LH wing. Refer to Figure 2. (4) Install the jacks to provide the support to lower the LH pylon. Refer to Figure 3. NOTE: The rear jib attachments, stays, adapter assemblies and tripod jacks ( ITEM GSE 459 ) are part of the powerplant removal and installation. If they are already installed on the pylon, make sure that they are correct installed before start to lower the pylon. (5) Remove the attaching parts of the LH pylon upper, lower and aft drag link. Refer to Figure 4. NOTE: The attaching parts of the LH pylon should be removed to let the LH pylon be lowered. (6) Carefully lower the LH pylon until you get the distance to gain access to the work area. Refer to Figure 3. Lower the pylon with extreme care and make sure that no items released and kept in the work area will be damaged during the accomplishment of this step. SERVICE BULLETIN SB190-57-0056 Page 28 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 29 F. PART I - LH WING FORWARD LOWER SKIN PANEL - REINFORCEMENT CAUTION: WHEN YOU START THE MODIFICATION RELATED TO PART I OF THIS SERVICE BULLETIN, YOU MUST COMPLETE IT BEFORE YOU START THE MODIFICATION RELATED TO PART II. (1) [RC] Do the structural reinforcement of the LH forward wing lower skin panel. Refer to Figure 5. (2) Rework the LH pylon side and aft fairings. Refer to Figure 9. NOTE: If the rework of the pylon fairings has already been done during the accomplishment of PART II of this bulletin, this rework is no longer necessary. G. PART II - LH WING REAR LOWER SKIN PANEL - REINFORCEMENT CAUTION: WHEN YOU START THE MODIFICATION RELATED TO PART II OF THIS SERVICE BULLETIN, YOU MUST COMPLETE IT BEFORE YOU START THE MODIFICATION RELATED TO PART I. (1) [RC] Do the structural reinforcement of the LH rear wing lower skin panel. Refer to Figure 6. (2) Rework the LH pylon side and aft fairings. Refer to Figure 9. NOTE: If the rework of the pylon fairings has already been done during the accomplishment of PART I of this bulletin, this rework is no longer necessary. H. APPLICABLE TO PART I AND PART II (1) Carefully lift the LH pylon until you get the height necessary to install the pylon attaching parts. Refer to Figure 3. NOTE: Lift the pylon with extreme care and make sure that no items released and kept in the work area will be damaged during the accomplishment of this step. (2) Install the attaching parts of the LH pylon. Refer to Figure 4. (3) Remove the tripod jacks from the LH pylon. Refer to Figure 3. NOTE: The rear jib attachments, stays, adapter assemblies and tripod jacks ( ITEM GSE 459 ) are part of the powerplant removal and installation. You can keep it installed on the pylon for the reinstallation of the powerplant. (4) Install the supports assemblies of the LH wing. Refer to Figure 2. (5) Connect the existing tube to the firewall hydraulic shutoff valve and rework the hydraulic tubes of the LH side. Refer to Figure 1. (6) Attach the items that follows: NOTE: 1) Remove all the protective cap/plug, plastic bags or equivalent component from the ducts and tubes. 2) Replace the O-rings as applicable during the tubes and ducts installation. (a) The screws and clamps of the applicable electrical harness. NOTE: Be careful when you handle the electrical harnesses and make sure that they are in a safe condition during the accomplishment of this bulletin. (b) The screws and clamps of the applicable fuel and hydraulic tubes. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 29 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 30 (c) The clamp shell that connects the tube of the engine fire extinguishing system to the drain valve. Refer to AMM TASK 20-10-13-400-801-A/400 - Clamp Shell (Typical) - Installation and to AMM TASK 26-21-13-400-801-A/400 - Engine Fire Extinguishing System Drain Valve Assembly - Installation. (d) The bonding jumpers of the LH pylon. Refer to AMM TASK 20-13-21-210-801-A/200 - Electrical Bonding Map - Standard Procedure. 1 Prepare the surface where the bonding jumpers will be installed, according to the applicable electrical bonding method. Refer to AMM TASK 20-13-21-910-801-A/200 - Types of Electrical Bonding and their Surface Preparation - Standard Procedures. 2 After bonding jumper installation, do the protection of the bonding areas according to AMM TASK 20-13-21-910-802-A/200 - Electrical Bonding Protection - Standard Procedures. 3 If applicable, do the fasteners head sealing with Class B2 Low-Density Polysulfide Sealant (AMS 3281) PR1776M B-2. Refer to SRM PART II 51-21-05 - FASTENER SEALING. (e) If applicable, the existing bonding jumpers installed on the tubes. 1 Prepare the surface where the bonding jumpers will be installed, according to the applicable electrical bonding method. Refer to AMM TASK 20-13-21-910-801-A/200 - Types of Electrical Bonding and their Surface Preparation - Standard Procedures. 2 After bonding jumper installation, do the protection of the bonding areas according to AMM TASK 20-13-21-910-802-A/200 - Electrical Bonding Protection - Standard Procedures. (f) The screws, clip mountings and electrical connectors of the applicable element sensor of the anti-icing and bleed leak detectors. Refer to AMM TASK 30-11-08-400-801-A/400 - Anti-Icing Leak Detectors - Installation and AMM TASK 36-21-02-400-801-A/400 - LH/RH Bleed Leak Detectors - Installation. NOTE: Be careful when you handle the element sensor not to damage them during the accomplishment of this bulletin. (g) The bleed duct. Refer to AMM TASK 36-11-04-400-801-A/400 - Engine Bleed Lines - Installation. (h) The clamp shell of the fuel feed line. Refer to AMM TASK 20-10-13-400-801-A/400 - Clamp Shell (Typical) - Installation and to AMM TASK 28-21-21-400-802-A/400 - Fuel Feed Line (Pylon) - Installation. (i) The clamp shell of the motive-flow supply line. Refer to AMM TASK 28-21-19-400-802- A/400 - Motive-Flow Supply Line (Pylon) - Installation. (j) The screws and clamps that attach the tube of the motive-flow supply line to the pylon structure. (7) Install the items that follow: (a) The support blocks of the hydraulic tubes. Refer to AMM TASK 20-10-03-400-801-A/400 - Tubing - Installation. (b) The fairings of the LH wing leading edge. Refer to AMM TASK 57-49-02-400-802-A/400 - Slat Track Cover - Installation. SERVICE BULLETIN SB190-57-0056 Page 30 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 31 (c) The LH wing anti-ice ducts. Refer to AMM TASK 30-11-07-400-801-A/400 - Wing Anti-Ice Ducts - Installation. (d) The LH slat torque tube (S7). Refer to AMM TASK 27-81-03-400-801-A/400 - Slat Torque Tube - Installation. (e) The LH engine. Refer to AMM TASK 71-00-01-400-801-B/400 - Powerplant - Installation. (f) The LH thrust reverser. Refer to AMM TASK 78-30-01-400-801-A/400 - Thrust Reverser - Installation. (g) The LH pylon aft fairings. Refer to AMM TASK 54-50-23-400-801-B/400 - Pylon Aft Fairings - Installation. (h) The LH pylon side fairings. Refer to AMM TASK 54-50-22-400-801-A/400 - Pylon Side Fairings - Installation. (i) The LH pylon forward fairings. Refer to AMM TASK 54-50-21-400-801-A/400 - Pylon Forward Fairings - Installation. (8) Install access panel 521EB. Refer to AMM TASK 28-11-03-400-801-A/400 - Fuel Tank Access Panel - Installation. (9) Do the tank leakage test. Refer to AMM TASK 28-11-00-790-802-A/500 - Wing Tank - Defueled Tank Leakage Check or AMM TASK 28-11-00-790-801-A/600 - Wing Tank - Fueled Tank Leakage Check. (10) Do the engine alignment and incidence check. Refer to AMM TASK 51-50-00-800-801-B/600 - Aircraft Alignment Check - Inspection/Check. I. APPLICABLE TO PART III AND IV (1) Remove access panel 621EB. Refer to AMM TASK 06-44-00-800-801-A/100 - Wing Access Doors and Panels and AMM TASK 28-11-03-000-801-A/400 - Fuel Tank Access Panel - Removal. (2) Remove and keep the items that follow to get access to the work area: (a) The RH pylon forward fairings. Refer to AMM TASK 54-50-21-000-801-A/400 - Pylon Forward Fairings - Removal. (b) The RH pylon side fairings. Refer to AMM TASK 54-50-22-000-801-A/400 - Pylon Side Fairings - Removal. (c) The RH pylon aft fairings. Refer to AMM TASK 54-50-23-000-801-B/400 - Pylon Aft Fairings - Removal. (d) The RH thrust reverser. Refer to AMM TASK 78-30-01-000-801-A/400 - Thrust Reverser - Removal. (e) The RH engine. Refer to AMM TASK 71-00-01-000-801-B/400 - Powerplant - Removal. (f) The RH slat torque tube (S7). Refer to AMM TASK 27-81-03-000-801-A/400 - Slat Torque Tube - Removal. (g) The applicable RH wing anti-ice ducts. Refer to AMM TASK 30-11-07-000-801-A/400 - Wing Anti-Ice Ducts - Removal. (h) The applicable fairings of the RH wing leading edge. Refer to AMM TASK 57-49-02-000-802-A/400 - Slat Track Cover - Removal. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 31 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 32 (i) The applicable support blocks of the hydraulic tubes. Refer to AMM TASK 20-10-03-000-801-A/400 - Tubing - Removal. NOTE: With a commercially available tape or equivalent component, do the protection of the existing tubes installed in the area near the lower link fuse pins. Do it to prevent damage to the tubes during the rework. (3) Release, as necessary, the items that follow, installed near and/or at the pylon area, to get access to the work area: NOTE: 1) If you completely remove any item with its parts from the aircraft, make sure that you mark its initial position of assembly before removal. Do it to prevent the wrong installation after the rework. 2) With protective cap/plug, plastic bags or equivalent component, do the protection of the applicable ducts and tubes to prevent leak splash and/or their contamination. (a) The screws and clamps of the applicable electrical harness. NOTE: Be careful when you handle the electrical harnesses and make sure that they are in a safe condition during the accomplishment of this bulletin. (b) The screws and clamps of the applicable fuel and hydraulic tubes. (c) The clamp shell that connects the tube of the engine fire extinguishing system to the drain valve. Refer to AMM TASK 20-10-13-000-801-A/400 - Clamp Shell (Typical) - Removal and to AMM TASK 26-21-13-000-801-A/400 - Engine Fire Extinguishing System Drain Valve Assembly - Removal. (d) The existing bonding jumpers of the RH pylon. Refer to AMM TASK 20-13-21-210-801- A/200 - Electrical Bonding Map - Standard Procedure and to SRM PART II 51-21-07 - SEALING REMOVAL. (e) If applicable, the existing bonding jumpers installed on the tubes. (f) The screws, clip mountings and electrical connectors of the applicable element sensor of the anti-icing and bleed leak detectors. Refer to AMM TASK 30-11-08-000-801-A/400 - Anti-Icing Leak Detectors - Removal and AMM TASK 36-21-02-000-801-A/400 - LH/RH Bleed Leak Detectors - Removal. NOTE: Be careful when you handle the element sensor to not damage them during the accomplishment of this bulletin. (g) The applicable bleed duct. Refer to AMM TASK 36-11-04-000-801-A/400 - Engine Bleed Lines - Removal. (h) The clamp shell of the fuel feed line. Refer to AMM TASK 20-10-13-000-801-A/400 - Clamp Shell (Typical) - Removal and to AMM TASK 28-21-21-000-802-A/400 - Fuel Feed Line (Pylon) - Removal. (i) The clamp shell of the motive-flow supply line. Refer to AMM TASK 28-21-19-000-802- A/400 - Motive-Flow Supply Line (Pylon) - Removal. (j) The applicable screws and clamps that attach the tube of the motive-flow supply line to the pylon structure. NOTE: Do it to get access to remove the existing bolt that attaches the RH pylon upper link outboard rod assy to the RH pylon. SERVICE BULLETIN SB190-57-0056 Page 32 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 33 (k) Disconnect the existing tube from the firewall hydraulic shutoff valve and cut the applicable hydraulic tubes of the RH side. Refer to Figure 1. (l) Release the applicable supports assemblies of the RH wing. Refer to Figure 2. (4) Install the jacks to provide the support to lower the RH pylon. Refer to Figure 3. NOTE: The rear jib attachments, stays, adapter assemblies and tripod jacks ( ITEM GSE 459 ) are part of the powerplant removal and installation. If they are already installed on the pylon, make sure that they are correctly installed before you start to lower the pylon. (5) Remove the attaching parts of the RH pylon upper, lower and aft drag link. Refer to Figure 4. NOTE: The attaching parts of the RH pylon should be removed to let the RH pylon be lowered. (6) Carefully lower the RH pylon until you get the distance necessary to gain access to the work area. Refer to Figure 3. Lower the pylon with extreme care and make sure that no items released and kept in the work area will be damaged during the accomplishment of this step. J. PART III - RH WING FORWARD LOWER SKIN PANEL - REINFORCEMENT CAUTION: WHEN YOU START THE MODIFICATION RELATED TO PART III OF THIS SERVICE BULLETIN, YOU MUST COMPLETE IT BEFORE YOU START THE MODIFICATION OF PART IV. (1) [RC] Do the structural reinforcement of the RH forward wing lower skin panel. Refer to Figure 5. (2) Rework the RH pylon side and aft fairings. Refer to Figure 9. NOTE: If the rework of the pylon fairings has already been done during the accomplishment of PART IV of this bulletin, this rework is no longer necessary. K. PART IV - RH WING REAR LOWER SKIN PANEL - REINFORCEMENT CAUTION: WHEN YOU START THE MODIFICATION RELATED TO PART IV OF THIS SERVICE BULLETIN, YOU MUST COMPLETE IT BEFORE YOU START THE MODIFICATION OF PART III. (1) [RC] Do the structural reinforcement of the RH rear wing lower skin panel. Refer to Figure 6. (2) Rework the RH pylon side and aft fairings. Refer to Figure 9. NOTE: If the rework of the pylon fairings has already been done during the accomplishment of PART III of this bulletin, this rework is no longer necessary. L. APPLICABLE TO PART III AND IV (1) Carefully lift the RH pylon until you get the height necessary to install the pylon attaching parts. Refer to Figure 3. NOTE: Lift the pylon with extreme care and make sure that no items released and kept in the work area will not be damaged during the accomplishment of this step. (2) Install the attaching parts of the RH pylon. Refer to Figure 4. (3) Remove the tripod jacks from the RH pylon. Refer to Figure 3. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 33 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 34 NOTE: The rear jib attachments, stays, adapter assemblies and tripod jacks ( ITEM GSE 459 ) are part of the powerplant removal and installation. You can keep it installed on the pylon for the reinstallation of the powerplant. (4) Install the supports assemblies of the RH wing. Refer to Figure 2. (5) Connect the existing tube to the firewall hydraulic shutoff valve and rework the hydraulic tubes of the RH side. Refer to Figure 1. (6) Attach the items that follows: NOTE: 1) Remove all the protective cap/plug, plastic bags or equivalent component from the ducts and tubes. 2) Replace the O-rings as applicable during the tubes and ducts installation. (a) The screws and clamps of the applicable electrical harness. NOTE: Be careful when you handle the electrical harnesses and make sure that they are in a safe condition during the accomplishment of this bulletin. (b) The screws and clamps of the applicable fuel and hydraulic tubes. (c) The clamp shell that connects the tube of the engine fire extinguishing system to the drain valve. Refer to AMM TASK 20-10-13-400-801-A/400 - Clamp Shell (Typical) - Installation and to AMM TASK 26-21-13-400-801-A/400 - Engine Fire Extinguishing System Drain Valve Assembly - Installation. (d) The bonding jumpers of the RH pylon. Refer to AMM TASK 20-13-21-210-801-A/200 - Electrical Bonding Map - Standard Procedure. 1 Prepare the surface where the bonding jumpers will be installed, according to the applicable electrical bonding method. Refer to AMM TASK 20-13-21-910-801-A/200 - Types of Electrical Bonding and their Surface Preparation - Standard Procedures. 2 After bonding jumper installation, do the protection of the bonding areas according to AMM TASK 20-13-21-910-802-A/200 - Electrical Bonding Protection - Standard Procedures. 3 If applicable, do the fasteners head sealing with Class B2 Low-Density Polysulfide Sealant (AMS 3281) PR1776M B-2. Refer to SRM PART II 51-21-05 - FASTENER SEALING. (e) If applicable, the existing bonding jumpers installed on the tubes. 1 Prepare the surface where the bonding jumpers will be installed, according to the applicable electrical bonding method. Refer to AMM TASK 20-13-21-910-801-A/200 - Types of Electrical Bonding and their Surface Preparation - Standard Procedures. 2 After bonding jumper installation, do the protection of the bonding areas according to AMM TASK 20-13-21-910-802-A/200 - Electrical Bonding Protection - Standard Procedures. (f) The screws, clip mountings and electrical connectors of the applicable element sensor of the anti-icing and bleed leak detectors. Refer to AMM TASK 30-11-08-400-801-A/400 - Anti-Icing Leak Detectors - Installation and AMM TASK 36-21-02-400-801-A/400 - LH/RH Bleed Leak Detectors - Installation. SERVICE BULLETIN SB190-57-0056 Page 34 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 35 NOTE: Be careful when you handle the element sensor to not damage them during the accomplishment of this bulletin. (g) The bleed duct. Refer to AMM TASK 36-11-04-400-801-A/400 - Engine Bleed Lines - Installation. (h) The clamp shell of the fuel feed line. Refer to AMM TASK 20-10-13-400-801-A/400 - Clamp Shell (Typical) - Installation and to AMM TASK 28-21-21-400-802-A/400 - Fuel Feed Line (Pylon) - Installation. (i) The clamp shell of the motive-flow supply line. Refer to AMM TASK 28-21-19-400-802- A/400 - Motive-Flow Supply Line (Pylon) - Installation. (j) The screws and clamps that attach the tube of the motive-flow supply line to the pylon structure. (7) Install the items that follows: (a) The support blocks of the hydraulic tubes. Refer to AMM TASK 20-10-03-400-801-A/400 - Tubing - Installation. (b) The fairings of the RH wing leading edge. Refer to AMM TASK 57-49-02-400-802-A/400 - Slat Track Cover - Installation. (c) The RH wing anti-ice ducts. Refer to AMM TASK 30-11-07-400-801-A/400 - Wing Anti-Ice Ducts - Installation. (d) The RH slat torque tube (S7). Refer to AMM TASK 27-81-03-400-801-A/400 - Slat Torque Tube - Installation. (e) The RH engine. Refer to AMM TASK 71-00-01-400-801-B/400 - Powerplant - Installation. (f) The RH thrust reverser. Refer to AMM TASK 78-30-01-400-801-A/400 - Thrust Reverser - Installation. (g) The RH pylon aft fairings. Refer to AMM TASK 54-50-23-400-801-B/400 - Pylon Aft Fairings - Installation. (h) The RH pylon side fairings. Refer to AMM TASK 54-50-22-400-801-A/400 - Pylon Side Fairings - Installation. (i) The RH pylon forward fairings. Refer to AMM TASK 54-50-21-400-801-A/400 - Pylon Forward Fairings - Installation. (8) Install access panel 621EB. Refer to AMM TASK 28-11-03-400-801-A/400 - Fuel Tank Access Panel - Installation. (9) Do the tank leakage test. Refer to AMM TASK 28-11-00-790-802-A/500 - Wing Tank - Defueled Tank Leakage Check or AMM TASK 28-11-00-790-801-A/600 - Wing Tank - Fueled Tank Leakage Check. (10) Do the engine alignment and incidence check. Refer to AMM TASK 51-50-00-800-801-B/600 - Aircraft Alignment Check - Inspection/Check. M. Lower the aircraft. Refer to AMM TASK 07-10-01-500-802-A/200 - Complete Aircraft Lowering - Maintenance Practices. N. Put the aircraft back to a serviceable condition. O. Write the accomplishment of PART I and/or PART II and/or PART III and/or PART IV of this bulletin in the applicable documents. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 35 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 36 NOTE: 1) Please use the online SB evaluation form available on the FlyEmbraer portal ( http:// www.flyembraer.com). Go to "Maintenance > eTechPubs > Utilities > SB Evaluation Form" to inform us about the SBs that you have incorporated in your fleet, as well as the difficulties found during the SB incorporation. This will allow Embraer to consider your aircraft configuration when providing future modifications. Your feedback will be much appreciated to improve the quality of Embraer modifications. SERVICE BULLETIN SB190-57-0056 Page 36 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 37 FIGURE 1 - REWORK OF THE HYDRAULIC SYSTEM (Sheet 1 of 7) WARNING: ALWAYS PUT ON GLOVES AND GOGGLES TO MAKE SURE THAT THE SKYDROL DOES NOT TOUCH YOU. SKYDROL IS CORROSIVE AND CAN CAUSE INJURIES TO YOUR EYES AND SKIN. CAUTION: PUT CAPS ON ALL LINES AND FITTINGS AND MAKE SURE THAT THE AREA IS CLEAN AND FREE OF ALL UNWANTED FLUID. DIRT CAN CAUSE SYSTEM CONTAMINATION, LEAKAGE, AND DAMAGE TO COMPONENTS. 1. Do the modifications of the hydraulic system of the LH side as follows: (a) Release the applicable items from their attaching points and cut the hydraulic tubes installed at the LH wing as follows: NOTE: 1) If you completely remove any item with its parts from the aircraft, make sure that you mark its initial position of assembly before removal. Do it to prevent the wrong installation after the rework. 2) Do the steps below to let the LH pylon be lowered. 1 Release the applicable hydraulic system support blocks from their attaching points as necessary, by removing and keeping the existing screws. Refer to Detail B (Pre-Mod). 2 Release the permaswage fitting as shown in Detail B (Pre-Mod). 3 Cut the applicable hydraulic tubes observing the dimensions of Detail B (Pre-Mod). Refer to AMM TASK 20-10-03-300-801-A/800 - Tubing - Repair. 4 Release the parts that connect the existing tube to the firewall hydraulic shutoff valve. Refer to Detail D (Pre-Mod) (Typical) and to AMM TASK 29-11-11-000-801-A/400 - Firewall Hydraulic Shutoff Valve - Removal. 5 Do the protection of all the open tubes end with plastic bags, cap/plugs or equivalent component to prevent leak splash and/or tubes contamination. Refer to Detail C (Pre-Mod). (b) Install the applicable items to their attaching points and rework the hydraulic tubes of the LH wing as follows: NOTE: The steps below must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. 1 Remove all the protective cap/plug, plastic bags or equivalent component from the tubes. 2 Rework the hydraulic tubes according to Detail B (POST-MOD). Refer to AMM TASK 20-10-03-300-801-A/800 - Tubing - Repair. 3 Install the applicable hydraulic system support blocks on their respective positions. Refer to Detail B (POST-MOD). 4 Install the permaswage fitting as shown in Detail B (POST-MOD). 5 Install the parts that connect the existing tube to the firewall hydraulic shutoff valve. Refer to Detail E (POST-MOD) (Typical) and to AMM TASK 29-11-11-400-801-A/400 - Firewall Hydraulic Shutoff Valve - Installation. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 37 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 38 FIGURE 1 - REWORK OF THE HYDRAULIC SYSTEM (Sheet 2 of 7) 2. Do the modifications of the hydraulic system of the RH side as follows: (a) Release the applicable items from their attaching points and cut the hydraulic tubes installed at the RH wing as follows: NOTE: 1) If you completely remove any item with its parts from the aircraft, make sure that you mark its initial position of assembly before removal. Do it to prevent the wrong installation after the rework. 2) Do the steps below to let the RH pylon be lowered. 1 Release the applicable hydraulic system support blocks from their attaching points as necessary, by removing and keeping the existing screws. Refer to Detail F (Pre-Mod). 2 Cut the applicable hydraulic tubes observing the dimensions of Detail F (Pre-Mod). Refer to AMM TASK 20-10-03-300-801-A/800 - Tubing - Repair. 3 Release the parts that connect the existing tube to the firewall hydraulic shutoff valve. Refer to Detail D (Pre-Mod) (Typical) and to AMM TASK 29-11-11-000-801-A/400 - Firewall Hydraulic Shutoff Valve - Removal. 4 Do the protection of all the open tubes end with plastic bags, cap/plugs or equivalent component to prevent leak splash and/or tubes contamination. Refer to Detail G (Pre-Mod). (b) Install the applicable items to their attaching points and rework the hydraulic tubes of the RH wing as follows: NOTE: The steps below must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. 1 Remove all the protective cap/plug, plastic bags or equivalent component from the tubes. 2 Rework the hydraulic tubes according to Detail F (POST-MOD). Refer to AMM TASK 20-10-03-300-801-A/800 - Tubing - Repair. 3 Install the applicable hydraulic system support blocks to their respective positions. Refer to Detail F (POST-MOD). 4 Install the parts that connect the existing tube to the firewall hydraulic shutoff valve. Refer to Detail E (POST-MOD) (Typical) and to AMM TASK 29-11-11-400-801-A/400 - Firewall Hydraulic Shutoff Valve - Installation. SERVICE BULLETIN SB190-57-0056 Page 38 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 39 FIGURE 1 - REWORK OF THE HYDRAULIC SYSTEM (Sheet 3 of 7) EM170SB540344B.DGN ZONE 419 A A ZONE 429 TYPICAL A BCFG LH PYLON (REF.) AFT−DRAG LINK (REF.) ±85.0 D (3.3465 ± 0.1968 in) (REF.) HYDRAULICTUBES (CUT) SUPPORT−BLOCK (RELEASE) PERMASWAGE FITTING (RELEASE) 104.0 ± 5.0 mm (4.095 ± 0.1968 in) (REF.) PRE − MOD B 5.0 (LH SIDE) 1 1 1 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 39 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 40 FIGURE 1 - REWORK OF THE HYDRAULIC SYSTEM (Sheet 4 of 7) EM170SB540345C.DGN TUBE (REF.) FIREWALL SHUTOFF VALVE (RELEASE) LOCK WIRE PN MS20995C32 (REMOVE AND DISCARD) SUPPORT (REF.) PRE − MOD D TYPICAL 1 2 REFER TO AMM PART II 29 −11−11−04 FOR FIREWALL SHUTOFF VALVE RELEASE. PRE − MOD C (LH SIDE) LH PYLON (REF.) 1 12 2 12 DO THE PROTECTION OF ALL THE OPEN TUBES END WITH PLASTIC BAGS, CAP/PLUGS OR EQUIVALENT COMPONENTS TO PREVENT LEAK SPLASH AND/OR TUBES CONTAMINATION. SERVICE BULLETIN SB190-57-0056 Page 40 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 41 FIGURE 1 - REWORK OF THE HYDRAULIC SYSTEM (Sheet 5 of 7) EM170SB540346C.IDR APPLY TORQUE OF 75.13 TO 83.04 N.m (665 TO 735 lb.in). REFER TO AMM PART II 20-10-03-04 FOR HYDRAULIC TUBES REWORK. REFER TO AMM PART II 29-11-11-04 FOR FIREWALL SHUTOFF VALVE INSTALLATION. 3 4 5 6 PERMASWAGE FITTING (INSTALL) SUPPORT-BLOCK (INSTALL) AFT DRAG LINK (REF.) LH PYLON (REF.) TUBE (REF.) FIREWALL SHUTOFF VALVE (INSTALL) SUPPORT (REF.) 3 E TYPICAL POST - MOD B POST - MOD 6 E PERMASWAGE UNION PN D10036-10 (INSTALL) 1 35 1 35 1 35 1 34 (LH SIDE) LOCKWIRE PN MS20995C32 (INSTALL) PERMASWAGE UNION PN D10036-06 (INSTALL) PERMASWAGE UNION PN D10036-08 (INSTALL) 1 2 1 2 REMOVE ALL THE PROTECTIVE PLASTIC BAGS, CAP/PLUGS OR EQUIVALENT COMPONENTS FROM THE TUBES ENDS. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 41 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 42 FIGURE 1 - REWORK OF THE HYDRAULIC SYSTEM (Sheet 6 of 7) EM170SB540347D.IDR PRE - MOD F (RH SIDE) PRE - MOD G 1 (RH SIDE) 85.0 ± 5.0 mm (3.3465 ± 0.1968 in) (REF.) 112.0 ± 5.0 mm (4.4094 ± 0.1968 in) (REF.) RH PYLON (REF.) AFT DRAG LINK (REF.) HYDRAULIC TUBES (CUT) 2 SUPPORT-BLOCK (RELEASE) 2 D 1 RH PYLON (REF.) DO THE PROTECTION OF ALL THE OPEN TUBES END WITH PLASTIC BAGS, CAP/PLUGS OR EQUIVALENT COMPONENTS TO PREVENT LEAK SPLASH AND/OR TUBES CONTAMINATION. SERVICE BULLETIN SB190-57-0056 Page 42 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 43 FIGURE 1 - REWORK OF THE HYDRAULIC SYSTEM (Sheet 7 of 7) EM170SB540348C.IDR POST - MOD F (RH SIDE) 3 5 RH PYLON (REF.) AFTDRAG LINK (REF.) PERMASWAGE UNION PN D10036-10 (INSTALL) PERMASWAGE UNION PN D10036-06 (INSTALL) 35 PERMASWAGE UNION PN D10036-08 (02 POSITIONS) (INSTALL) SUPPORT-BLOCK (INSTALL) 2 HYDRAULIC TUBES (REF.) REFER TO AMM PART II 20-10-03-04 FOR HYDRAULIC TUBES REWORK. HYDRAULIC TUBES (REF.) 2 352 352 REMOVE ALL THE PROTECTIVE PLASTIC BAGS, CAP/PLUGS OR EQUIVALENT COMPONENTS FROM THE TUBES ENDS. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 43 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 44 FIGURE 2 - SUPPORT ASSY REMOVAL/INSTALLATION (Sheet 1 of 5) 1. Remove and keep the existing LH supports assemblies from their attaching points. Refer to Details B, C, D and E. NOTE: Do the steps below to let the LH pylon be lowered. 2. Install the existing LH supports assemblies to their attaching points. Refer to Details B, C, D and E. NOTE: This step must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. 3. Remove and keep the existing RH supports assemblies from their attaching points. Refer to Details G, H, J and K. NOTE: Do the steps below to let the RH pylon be lowered. 4. Install the existing RH supports assemblies to their attaching points. Refer to Details G, H, J and K. NOTE: This step must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. SERVICE BULLETIN SB190-57-0056 Page 44 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 45 FIGURE 2 - SUPPORT ASSY REMOVAL/INSTALLATION (Sheet 2 of 5) EM170SB540318B.DGN A ZONE 521 RIB RIB 08 09 A B C D E B ZONE 621 F WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) C SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) SUPPORT ASSY (REF.) 12 12 12 12 12 12 12 12 SUPPORT ASSY (REF.) SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 45 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 46 FIGURE 2 - SUPPORT ASSY REMOVAL/INSTALLATION (Sheet 3 of 5) EM170SB540319B.DGN D E SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) SUPPORT ASSY (REF.) SUPPORT ASSY (REF.) SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) BONDING JUMPER (REF.) 12 12 12 12 12 12 12 12 12 12 12 12 SERVICE BULLETIN SB190-57-0056 Page 46 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 47 FIGURE 2 - SUPPORT ASSY REMOVAL/INSTALLATION (Sheet 4 of 5) EM170SB540320B.DGN RIB RIB 08 09 K J H G F G SUPPORT ASSY (REF.) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) H SUPPORT ASSY (REF.) SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) 34 34 34 34 34 34 34 34 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 47 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 48 FIGURE 2 - SUPPORT ASSY REMOVAL/INSTALLATION (Sheet 5 of 5) EM170SB540321B.DGN J K SUPPORT ASSY (REF.) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) SUPPORT ASSY (REF.) BONDING JUMPER (REF.) SCREW (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) WASHER (REMOVE AND KEEP) (INSTALL) SCREW (REMOVE AND KEEP) (INSTALL) 34 34 34 34 34 34 34 34 34 34 SERVICE BULLETIN SB190-57-0056 Page 48 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 49 FIGURE 3 - PYLON LOWERING AND LIFTING (Sheet 1 of 6) 1. Install the tripod jacks as follows. Refer to Details B, C and D. NOTE: The rear jib attachments, stays, adapter assemblies and tripod jacks ( ITEM GSE 459) are part of the powerplant removal and installation. If they are already installed on the pylon, make sure that they are correctly installed before you start to lower the pylon. (a) Make sure that the GSE bolts (04 positions) are in a good condition before you install them. (b) Install the LH and RH rear jib attachments to the pylon with the GSE bolt (02 positions for each rear jib attachment) and GSE washer (02 positions for each rear jib attachment). (c) Install the LH and RH stays to the pylon with the GSE stay attach bolt (01 position for each stay) and GSE washer (01 position for each stay). (d) Install the LH and RH stays to the LH and RH rear jib attachments with the pin (01 position for each stay). (e) Apply a torque of 18 - 21 N.m (60 - 190 lb.in) to the GSE bolt (04 positions) and GSE stay attach bolt (04 positions). NOTE: Make sure that the GSE bolts and GSE stay attach bolts are correctly installed before you apply the torque. (f) Install the adapter assembly (01 position for each side) of the tripod jack ( ITEM GSE 459) to the LH and RH rear jib attachments. (g) Install the pin (02 positions for each adapter) and lock them with the lock clip (02 positions for each adapter). (h) Install the tripod jack ( ITEM GSE 459) (01 position for each side) to the adapter assemblies. NOTE: Adjust the height of the tripod jack ( ITEM GSE 459) as applicable. (i) Install the pin (01 position for each tripod jack) and lock it with the lock clip (01 position for each tripod jack). (j) Install the tripod jacks to hold the pylon weight as follows. Refer to Details C and D. NOTE: For tripod jack specification refer to 2.F. TOOLING - PRICE AND AVAILABILITY. 1 Put the tripod jack (01 position) under the pylon forward structure. Refer to Detail C. a Use a wooden block (or similar material) between the tripod jack and pylon structure, to prevent damage to the pylon structure. b Apply pressure to the tripod jack until it touches the wooden block/pylon structure. NOTE: Make sure that the pylon weight is correctly hold. 2 Put the tripod jack (01 position) under the pylon aft structure. Refer to Detail D. a Use a wooden block (or similar material) between the tripod jack and pylon structure, to prevent damage to the pylon structure. b Apply pressure to the tripod jack until it touches the wooden block/pylon structure. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 49 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 50 FIGURE 3 - PYLON LOWERING AND LIFTING (Sheet 2 of 6) NOTE: Make sure that the pylon weight is correct hold. 2. Lower the pylon as follows: NOTE: 1) Make sure that all the components necessary to lower the LH/RH pylon are released or removed from the work area. If necessary, remove or release the applicable component(s) to let the LH/RH pylon be lowered. 2) Do the steps below carefully to prevent damage to the components near or in the work area. (a) At the same time, release the pressure of the tripod jacks (04 positions) to lower the pylon until you get the distance necessary to gain access to the work area. Refer to Detail E. 3. Lift the pylon until you get the height necessary to install the pylon attaching parts as follows: (a) At the same time, apply pressure to the tripod jacks (04 positions) to lift the pylon until you get the height necessary to install the pylon attaching parts. (b) Apply or release pressure from the tripod jacks (04 positions) as applicable to get the correct alignment between the pylon lugs and wing fittings. 4. Remove the tripod jacks as follows. Refer to Details B, C and D. NOTE: 1) The steps below must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. 2) The rear jib attachments, stays, adapter assemblies and tripod jacks ( ITEM GSE 459 ) are part of the powerplant removal and installation. You can keep it installed on the pylon for the reinstallation of the powerplant. (a) Remove the lock clip (01 position for each tripod jack) and the pin (01 position for each tripod jack). (b) Remove the tripod jack ( ITEM GSE 459) from the adapter assemblies. (c) Remove the lock clip (02 positions for each adapter) and pin (02 positions for each adapter) from the adapter assemblies. (d) Remove the LH and RH stays from the LH and RH rear jib attachments by removing the pin (01 position for each stay). (e) Remove the LH and RH stays from the pylon by removing the GSE stay attach bolt (01 position for each stay) and GSE washer (01 position for each stay). (f) Remove the LH and RH rear jib attachments from the pylon by removing the GSE bolt (02 positions for each rear jib attachment) and GSE washer (02 positions for each rear jib attachment). (g) Release the pressure from the tripod jacks (02 positions) to remove it from the pylon forward and aft structures. Refer to Details C and D. SERVICE BULLETIN SB190-57-0056 Page 50 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 51 FIGURE 3 - PYLON LOWERING AND LIFTING (Sheet 3 of 6) EM170SB540486A.IDR ZONES 419 429 A LH STAY LH REAR JIB ATTACHMENT RH REAR JIB ATTACHMENT RH STAY PYLON (REF.) B C D TRIPOD JACK TRIPOD JACK TRIPOD JACK TRIPOD JACK LEFT SIDE SHOWN RIGHT SIDE OPPOSITE A SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 51 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 52 FIGURE 3 - PYLON LOWERING AND LIFTING (Sheet 4 of 6) EM170SB540487A.IDR ADAPTER ASSY ADAPTER ASSY RH STAY LH STAY RH REAR IB ATTACHMENT LH REAR IB ATTACHMENT PIN LOCK CLIP PIN PIN GSE WASHER GSE STAY ATTACH BOLT GSE WASHER GSE BOLT LOCK CLIP PIN PIN PIN LOCK CLIP LOCK CLIP GSE STAY ATTACH BOLT GSE WASHER GSE BOLT GSE WASHER TRIPOD ACK TRIPOD ACK PYLON (REF.) 1 1 1 1 1 TORQUE 18 - 21 N.m (160 - 190 .in). SERVICE BULLETIN SB190-57-0056 Page 52 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 53 FIGURE 3 - PYLON LOWERING AND LIFTING (Sheet 5 of 6) EM170SB540488A.IDR D C 2 USE A WOODEN BLOCK (OR SIMILAR MATERIAL) BETWEEN THE TRIPOD ACK AND PYLON STRUCTURE, TO PREVENT DAMAGE TO THE PYLON STRUCTURE. TRIPOD ACK TRIPOD ACK PYLON AFT STRUCTURE (REF.) PYLON FWD STRUCTURE (REF.) 2 2 SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 53 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 54 FIGURE 3 - PYLON LOWERING AND LIFTING (Sheet 6 of 6) EM170SB540489A.IDR 1 LH/RH PYLON (REF.) 1 FITTING ASSY (REF.) 1 PYLON LUG (REF.) SWAGED BUSHING (REF.) CAREFULLY LOWER THE PYLON UNTIL YOU GET THE DISTANCE TO GAIN ACCESS TO THE WORK AREA. SERVICE BULLETIN SB190-57-0056 Page 54 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 55 FIGURE 4 - PYLON UPPER, LOWER AND AFT DRAG LINK - ATTACHING PARTS REMOVAL/INSTALLATION (Sheet 1 of 24) 1. Remove and keep or install the attaching parts of the LH/RH pylon lower link inboard fitting as follows: (a) Applicable to aircraft without the lock washer and L-profile installed. 1 Remove the attaching parts of the LH/RH pylon lower link inboard fitting. Refer to Detail B (Pre-Mod). NOTE: Do the steps below to let the LH/RH pylon be lowered. a Remove and discard cotter pin PN MS24665-374 (01 position) and washer PN NAS1149C1490R (as applicable). b Remove and keep fuse pin PN 190-15183-40X (01 position), plain bushing PN 190-33685-021 (01 position) and castellated nut PN PE22072L14 (01 position). 2 Install the attaching parts of the LH/RH pylon lower link inboard fitting . Refer to Detail B (POST-MOD). NOTE: The steps below must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. a Install the attaching parts of the LH/RH pylon lower link fitting inboard as follows: 1) The plain bushing PN 190-33685-021 (01 position). 2) The fuse pin PN 190-15183-40X (01 position). 3) The new washer PN NAS1149C1432R (as required). NOTE: Install washer PN NAS1149C1432R if it is necessary to install the cotter pin. 4) The castellated nut PN PE22072L14 (01 position). b Apply torque to the castellated nut PN PE22072L14 as follows: NOTE: Make sure that the fuse pin does not turn when you apply the torque. If necessary, safety the other side of the fuse pin with a proper wrench to make sure that it does not turn. 1) Turn the castellated nut PN PE22072L14 and measure the drag torque with a torque wrench. 2) Make sure that the drag torque is between 7.91 - 67.79 N.m (70 - 600 lb.in). NOTE: If the castellated nut PN PE22072L14 is not in the correct range, replace it with new one (same PN). 3) Add the drag torque value measured in 1.(a)2b1) Figure 4 to the standard torque of 50.8 to 73.4 N.m (450 to 650 lb.in) to get the final torque. 4) Apply the final torque to the castellated nut PN PE22072L14 with a torque wrench. Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - Maintenance Practices. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 55 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 56 FIGURE 4 - PYLON UPPER, LOWER AND AFT DRAG LINK - ATTACHING PARTS REMOVAL/INSTALLATION (Sheet 2 of 24) 5) Install a new cotter pin PN MS24665-374 (01 position). 6) Apply a drop of Yellow Torque Seal (MEP 09-068) F-925 to the threaded end of the fuse pin. 7) Apply a coat of Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15. (b) Applicable to aircraft with the lock washer and L-profile installed. 1 Remove the attaching parts of the LH/RH pylon lower link outboard fitting. Refer to Details C (Pre-Mod) and D. NOTE: Do the steps below to let the LH/RH pylon be lowered. a Remove and discard cotter pin PN MS24665-376 (01 position). b Remove and keep fuse pin PN 190-15183-40X (01 position), plain bushing PN 190-33685-023 (01 position), washer PN NAS1149C1432R (as applicable), castellated nut PN PE22072L14 (01 position), lock washer PN 191-28264-401 (01 position), L-profile PN 191-28265-001 (01 position) and screw PN NAS1802-04-5 (02 positions). 2 Install the attaching parts of the LH/RH pylon lower link inboard fitting. Refer to Details C (POST-MOD) and D. NOTE: The steps below must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. a Install the attaching parts of the LH/RH pylon lower link fitting inboard as follows: 1) The plain bushing PN 190-33685-023 (01 position). 2) The fuse pin PN 190-15183-40X (01 position). 3) The washer PN NAS1149C1432R (as required). NOTE: Install washer PN NAS1149C1432R if it is necessary to install the cotter pin. 4) The castellated nut PN PE22072L14 (01 position). 5) The lock washer PN 191-28264-401 (01 position). 6) The L-profile PN 191-28265-001 (01 position). 7) The screw PN NAS1802-04-5 (02 positions). b Apply torque to the castellated nut PN PE22072L14 as follows: NOTE: Make sure that the fuse pin does not turn when you apply the torque. If necessary, safety the other side of the fuse pin with a proper wrench to make sure that it will not turn. SERVICE BULLETIN SB190-57-0056 Page 56 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 57 FIGURE 4 - PYLON UPPER, LOWER AND AFT DRAG LINK - ATTACHING PARTS REMOVAL/INSTALLATION (Sheet 3 of 24) 1) Turn the castellated nut PN PE22072L14 and measure the drag torque with a torque wrench. 2) Make sure that the drag torque is between 7.91 - 67.79 N.m (70 - 600 lb.in). NOTE: If the castellated nut PN PE22072L14 is not in the correct range, replace it with new one (same PN). 3) Add the drag torque value measured in 1.(b)2b1) Figure 4 to the standard torque of 50.8 to 73.4 N.m (450 to 650 lb.in) to get the final torque. 4) Apply the final torque to the castellated nut PN PE22072L14 with a torque wrench. Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - Maintenance Practices. 5) Install a new cotter pin PN MS24665-376 (01 position). 6) Apply a drop of Yellow Torque Seal (MEP 09-068) F-925 to the threaded end of the fuse pin. 7) Apply a coat of Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15. (c) Applicable to aircraft with the lock washer, L-profile and internal shear pin with greater head installed. 1 Remove the attaching parts of the LH/RH pylon lower link inboard fitting. Refer to Details F (Pre-Mod), D and G. NOTE: Do the steps below to let the LH/RH pylon be lowered. a Remove the internal shear pin from the external shear pin as follows. Refer to Detail G. 1) Remove and discard the cotter pin PN MS24665-372 (01 position). 2) Remove and keep the castellated nut PN MS14145L8 (01 position), washer PN 170-16196-001 (01 position) 3) Remove and keep the internal shear pin PN 191-32677-001 (01 position). b Remove and discard cotter pin PN MS24665-376 (01 position). c Remove and keep the external shear pin PN 190-15182-003 (01 position), plain bushing PN 190-33685-023 (01 position), washer PN NAS1149C1432R (as applicable), castellated nut PN PE22072L14 (01 position), lock washer PN 191-28264-401 (01 position), L-profile PN 191-28265-001 (01 position) and screw PN NAS1802-04-5 (02 positions). 2 Install the attaching parts of the LH/RH pylon lower link inboard fitting. Refer to Details F (POST-MOD), D and G. NOTE: The steps below must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 57 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 58 FIGURE 4 - PYLON UPPER, LOWER AND AFT DRAG LINK - ATTACHING PARTS REMOVAL/INSTALLATION (Sheet 4 of 24) a Install the attaching parts of the LH/RH pylon lower link fitting inboard as follows: 1) The plain bushing PN 190-33685-023 (01 position). 2) The external shear pin PN 190-15182-003 (01 position). 3) The washer PN NAS1149C1432R (as required). NOTE: Install washer PN NAS1149C1432R if it is necessary to install the cotter pin. 4) The castellated nut PN PE22072L14 (01 position). 5) The lock washer PN 191-28264-401 (01 position). b Apply torque to the castellated nut PN PE22072L14 as follows: NOTE: Make sure that the fuse pin does not turn when you apply the torque. If necessary, safety the other side of the fuse pin with a proper wrench to make sure that it will not turn. 1) Turn the castellated nut PN PE22072L14 and measure the drag torque with a torque wrench. 2) Make sure that the drag torque is between 7.91 - 67.79 N.m (70 - 600 lb.in). NOTE: If the castellated nut PN PE22072L14 is not in the correct range, replace it with new one (same PN). 3) Add the drag torque value measured in 1.(c)2b1) Figure 4 to the standard torque of 50.8 to 73.4 N.m (450 to 650 lb.in) to get the final torque. 4) Apply the final torque to the castellated nut PN PE22072L14 with a torque wrench. Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - Maintenance Practices. c Install the internal shear pin PN 191-32677-001 (01 position) to the external shear pin PN 190-15182-003 (01 position) of the LH/RH pylon lower link inboard fitting. Refer to Detail G. NOTE: This step shall be done only after you make sure that the final torque was applied to the castellated nut PN PE22072L14. 1) Apply Corrosion Inhibiting Compound (MEP_09-075) COR-BAN 27L on the internal shear pin PN 191-32677-001 (01 position). NOTE: Make sure that the protruding threaded end of the internal shear pin is completely wet with Corrosion Inhibiting Compound (MEP_09-075) COR-BAN 27L. 2) Install the internal shear pin PN 191-32677-001 (01 position). 3) Install the washer PN 170-16196-001 (01 position) and castellated nut PN MS14145L8 (01 position). SERVICE BULLETIN SB190-57-0056 Page 58 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 59 FIGURE 4 - PYLON UPPER, LOWER AND AFT DRAG LINK - ATTACHING PARTS REMOVAL/INSTALLATION (Sheet 5 of 24) a) Safety the internal and external shear pins, through their cotter pin holes, with a proper tooling to prevent them from turning when you install the castellated nut PN MS14145L8, that attaches the internal shear pin to the external shear pin. NOTE: An example of tooling that you can use to safety the internal and external shear pins is a commercially available pin punch set. b) Apply sufficient torque to the assembly to make sure that it is correctly locked and make sure that the castellated nut is aligned for cotter pin installation. There is no specified torque for this assembly. c) Make sure that washer PN 170-16196-001 is completely locked after you tighten the assembly. a. If it is moving, apply the torque to the assembly again 1.(c)2c3)b) Figure 4. d Install a new cotter pin PN MS24665-372 (01 position). e Install a new cotter pin PN MS24665-376 (01 position). f Install the L-profile PN 191-28265-001 (01 position) on the lock washer PN 191-28264-401 (01 position) with the screw PN NAS1802-04-5 (02 positions). g Apply a drop of Yellow Torque Seal (MEP 09-068) F-925 to the threaded end of the fuse pin. h Apply a coat of Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15. 2. Remove and keep or install the attaching parts of the LH/RH pylon lower link outboard fittings as follows: (a) Applicable to aircraft without the lock washer and L-profile installed. 1 Remove the attaching parts of the LH/RH pylon lower link outboard fitting. Refer to Detail B (Pre-Mod). NOTE: Do the steps below to let the LH/RH pylon be lowered. a Remove and discard cotter pin PN MS24665-374 (01 position) and washer PN NAS1149C1490R (as applicable). b Remove and keep fuse pin PN 190-15180-40X (01 position), plain bushing PN 190-33686-021 (02 positions) and castellated nut PN PE22072L14 (01 position). 2 Install the attaching parts of the LH/RH pylon lower link outboard fitting. Refer to Detail B (POST-MOD). NOTE: The steps below must be done only after the rework of the wing lower skin is completed and the pylon is returned to its position. a Install the attaching parts of the LH/RH pylon lower link outboard fitting as follows: SERVICE BULLETIN Date: Dec 05, 2019 Revision No.: SB190-57-0056 Page 59 of 149 Copyright © by Embraer S.A. All rights reserved - See title page for details. ### Page 60 FIGURE 4 - PYLON UPPER, LOWER AND AFT DRAG LINK - ATTACHING PARTS REMOVAL/INSTALLATION (Sheet 6 of 24) 1) The plain bushing PN 190-33686-021 (02 positions). 2) The fuse pin PN 190-15180-40X (01 position). 3) The new washer PN NAS1149C1432R (as required). NOTE: Install washer PN NAS1149C1432R if it is necessary to install the cotter pin. 4) The castellated nut PN PE22072L14 (01 position). b Apply torque to the castellated nut PN PE22072L14 as follows: NOTE: Make sure that the fuse pin does not turn when you apply the torque. If necessary, safety the other side of the fuse pin with a proper wrench to make sure that it will not turn. 1) Turn the castellated nut PN PE22072L14 and measure the drag torque with a torque wrench. 2) Make sure that the drag torque is between 7.91 - 67.79 N.m (70 - 600 lb.in). NOTE: If the castellated nut PN PE22072L14 is not in the correct range, replace it with new one (same PN). 3) Add the drag torque value measured in 2.(a)2b1) Figure 4 to the standard torque of 50.8 to 73.4 N.m (450 to 650 lb.in) to get the final torque. 4) Apply the final torque to the castellated nut PN PE22072L14 with a torque wrench. Refer to AMM TASK 20-10-01-910-801-A/200 - Bolt Torque Data - Maintenance Practices. 5) Install a new cotter pin PN MS24665-376 (01 position). 6) Apply a drop of Yellow Torque Seal (MEP 09-068) F-925 to the threaded end of the fuse pin. 7) Apply a coat of Corrosion Inhibiting Compound, Type III (MEP 10-063) ARDROX AV-15. (b) Applicable to aircraft with the lock washer and L-profile installed. 1 Remove the attaching parts of the LH/RH pylon lower link outboard fitting. Refer to Details C (Pre-Mod) and E. NOTE: Do the steps below to let the LH/RH pylon be lowered. a Remove and discard cotter pin PN MS24665-376 (01 position). b Remove and keep fuse pin PN 190-15180-40X (01 position), plain bushing PN 190-33686-023 (02 positions), washer PN NAS1149C1432R (as applicable), castellated nut PN PE22072L14 (01 position), lock washer PN 191-28263-401 (01 position LH side) or PN 191-28263-402 (01 position RH side) as applicable, L-profile PN 191-28265-001 (01 position LH side) or PN 191-28265-002 (01 position RH side) as applicable, and screw PN NAS1802-04-5 (02 positions). SERVICE BULLETIN SB190-57-0056 Page 60 of 149 Date: Dec 05, 2019 Revision No.: Copyright © by Embraer S.A. All rights reserved - See title page for details. The text continues at https://openairdocs.org/service-documents/embraer/sb-190-57-0056/file/7b2f11be73fa.md?from=61 --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. 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