# Embraer Service Bulletin 190-36-0027 ## Copies (2) Copies the FAA filed in AD dockets on regulations.gov, newest revision first. A newer revision may exist. - Revision 02, part 1 of 2 ("Embraer SB 190-36-0027 Rev. 2 05Sep23_Part1"), 63 pages: PDF https://openairdocs.org/files/sha256/c7/4e/c74e0b80647c4d8bd0ff7175b1cf03697cadeb8beff6d5dd8c552c17936ae609; text https://openairdocs.org/service-documents/embraer/sb-190-36-0027/file/c74e0b80647c.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2024-1704, the docket of AD 2024-20-06. Not covered by OpenAirDocs’ CC0 dedication. - Revision 02, part 2 of 2 ("Embraer SB 190-36-0027 Rev. 2 05Sep23_Part2"), 57 pages: PDF https://openairdocs.org/files/sha256/46/93/469357beaacd77e01f40f59de63ec242066441da94775a6adf9f046b01ddc7ad; text https://openairdocs.org/service-documents/embraer/sb-190-36-0027/file/469357beaacd.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2024-1704, the docket of AD 2024-20-06. Not covered by OpenAirDocs’ CC0 dedication. ## Details - Manufacturer: [Embraer](https://openairdocs.org/service-documents/embraer.md) - Type: Service bulletin (Service Bulletin) - Number: 190-36-0027 - Latest revision known: 190-36-0027, Revision 02, dated September 5, 2023 (OpenAirDocs) - Page: https://openairdocs.org/service-documents/embraer/sb-190-36-0027 ## ADs that cite it (1) (OpenAirDocs) Newest first, with the revision each names, as OpenAirDocs read it from the AD's text. - [AD 2024-20-06](https://openairdocs.org/ad/2024-20-06.md), effective Nov 29, 2024: Revision 02 Also cited in [1 proposed AD](https://openairdocs.org/service-documents/embraer/sb-190-36-0027/proposed.md). ## Text (63 pages) Revision 02, part 1 of 2, the newest copy. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2024-1704, the docket of AD 2024-20-06. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N. ### Page 1 1. DESCRIPTION This sheet transmits Revision 02 to Service Bulletin 190-36-0027. This is a complete reissue of the Bulletin. 2. ADDITIONAL ACTION Aircraft that have complied with the previous issue of this bulletin do not need any additional action. 3. RECORD OF REVISION Basic issue: Apr 30, 2021. Revision 01: Dec 16, 2022. Revision 02: Sep 05, 2023. 4. HIGHLIGHTS The topics, affected pages, and a brief description of the content-related changes introduced by this revision are presented below. Revision bars are put in the left margin of each page to show the location of the significant changes. Text displacement and text format changes are not indicated. TOPIC/PAGE DESCRIPTION OF REVISION 1. PLANNING INFORMATION 1.C. REASON / 02 Added reason for Revision 02. 1.D. DESCRIPTION / 03 thru 08 Updated the acronyms related to AIPC. 1.D. DESCRIPTION / 03 thru 07 Updated note related to deactivation. 1.E. COMPLIANCE / 08 and 09 Updated the Compliance information. 1.J. REFERENCES / 12 Updated list of references. 3. ACCOMPLISHMENT INSTRUCTIONS / 18, 19, 20, 22 thru 40 Included information related to RC. 3. ACCOMPLISHMENT INSTRUCTIONS / 20, 22 thru 27, 29, 30, 32, 33, 35, 36 and 39 Included description EICAS display. 3. ACCOMPLISHMENT INSTRUCTIONS / 20, 24, 27, 30, 33, 36 and 39 Updated note related to deactivation. 3. ACCOMPLISHMENT INSTRUCTIONS / 22, 25, 27, 30, 33, 36 and 39 Included AIPC reference. 3. ACCOMPLISHMENT INSTRUCTIONS / 20, 24, 26, 29, 32 and 35 Included FIM task reference. 3. ACCOMPLISHMENT INSTRUCTIONS / 35 Corrected the display where the BLEED 2 LEAK and PACK 2 LEAK messages are shown. 3. ACCOMPLISHMENT INSTRUCTIONS / 41 Updated sentence according to current standard. TRANSMITTAL LETTER Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 1 of 2 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 2 (Continued) TOPIC/PAGE DESCRIPTION OF REVISION Figure 15 / 81 Corrected illustration to include information related LOOP 3. Figure 17 / 94 Corrected illustration to include information related LOOP 2. TRANSMITTAL LETTER SB190-36-0027 Page 2 of 2 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 3 PNEUMATIC - INSPECTION AND REPLACEMENT OF OVERHEAT DETECTION SYSTEM (ODS) SENSING ELEMENTS 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. Export 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 thru 19000108, 19000110 thru 19000139, 19000141 thru 19000158, 19000160 thru 19000176, 19000178 thru 19000202, 19000204 thru 19000213, 19000215 thru 19000224, 19000226 thru 19000235, 19000237 thru 19000242, 19000244 thru 19000260, 19000262 thru 19000276, 19000279 thru 19000295, 19000297 thru 19000306, 19000308 thru 19000316, 19000318 thru 19000361, 19000363 thru 19000437, 19000439 thru 19000452, 19000454 thru 19000466, 19000468 thru 19000525, 19000527 thru 19000533, 19000535 thru 19000558, 19000560 thru 19000570, 19000572 thru 19000610, 19000612 thru 19000631, 19000633 thru 19000640, 19000642 thru 19000655, 19000657 thru 19000682, 19000684 thru 19000690, 19000692 thru 19000694, 19000696 thru 19000704, 19000706 thru 19000708, 19000710 thru 19000731, and 19000733 thru 19000773. Affected component: Sensing element, All Part Numbers and all serial numbers. In-production effectivity: This bulletin does not affect any in-production aircraft. B. CONCURRENT REQUIREMENTS None. C. REASON (1) HISTORY Embraer has been informed by supplier that a quality escape has occurred in its manufacturing line, and the Overheat Detection System (ODS) sensors have been affected. Due to this quality escape, a defective sensor may present a latent failure which is not detectable through CMC or EICAS messages. A degradation of the bleed leak detection can occur. In that case, a leak may not be detected if it occurs where the sensor is failed. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 1 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 4 Also, this condition can cause damage to the bleed leak detection system and under certain conditions, there is a possibility to affect flight safety. (2) OBJECTIVE To give instructions to inspect the ODS sensing elements of the aircraft bleed lines and replace them as necessary. (3) EXPECTED BENEFITS Ensure that the ODS system is functioning correctly. (4) REVISION HISTORY REVISION 01: This revision has been issued to increase compliance time to accomplish SB PARTs I, II, III and IV. Also the SB text and references were updated to be more clear. REVISION 02: This revision has been issued to: – Update the Compliance information. – Update the Service Bulletin steps that comply with the RC (Required for Compliance). – Corrected the display where the BLEED 2 LEAK and PACK 2 LEAK messages are shown. Updated from CMC screen to EICAS display. – Updated ACROs related to AIPC.Also, included AIPC references. – Editorial corrections. D. DESCRIPTION This Bulletin is divided into 8 PARTS, as follows: PART I INSPECTION AND REPLACEMENT OF THE APU BLEED LINE ODSSENSING ELEMENTS LOCATED AT MID-BAY, AFT-BAY AND STUB Applicable to: 1.A. SB EFFECTIVITY The modification presented in PART I of this bulletin consists of the inspection of the sensing elements of the Overheat Detection System (ODS) related to APU bleed line installed at mid-bay, aft-bay, and stub areas. NOTE: Inspection of the ODS related to the APU bleed line, installed at non-pressurized areas and cargo-compartment is presented in PART VII of this bulletin. This PART presents the following actions: (1) Check if there is any short or open condition (True) in the related APU loops. (a) If there are any short or open conditions on CMC, two actions are possible to be done: 1 Do the troubleshooting according to FIM (Fault Isolation Manual) and perform the sensing elements inspection described in step (b), or; NOTE: After FIM procedure accomplishment it is necessary to do the inspection of sensing element. SERVICE BULLETIN SB190-36-0027 Page 2 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 5 2 Deactivate the sensing elements according to wiring modification. If the sensing elements were deactivated, it will be necessary to activate them according to PART VIII of this Bulletin. NOTE: In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). (b) If there are no short or open conditions (False) on CMC, do as follows: 1 Get access to the sensing elements, by removing the applicable access and floor panels; 2 Perform the inspection on the active sensing elements according to section 3. ACCOMPLISHMENT INSTRUCTIONS in order to detect the possible sensing element failures; 3 Replace the failed sensing elements with a new one with the same PN or with a PN presented in the Aircraft Illustrated Parts Catalog (AIPC), according to the applicable AMM task. To get access to the work areas, it is necessary to remove/open panels according to Table Affected PN x Access Panel for PART I. PART II INSPECTION AND REPLACEMENT OF THE ODS SENSINGELEMENTS OF LH AND RH WING ANTI-ICE SUPPLY DUCTS Applicable to: 1.A. SB EFFECTIVITY The modification presented in PART II of this bulletin consists of the inspection of the sensing elements of the Overheat Detection System (ODS) related to LH and RH wing anti-ice system installed near slat 2 and pylon. This PART presents the following actions: (1) Check if there is any short or open condition (True) in the LH and RH Wing anti-ice supply ducts. (a) If there are any short or open conditions on CMC, two actions are possible to be done: 1 Do the troubleshooting according to FIM (Fault Isolation Manual) and perform the sensing elements inspection, or; NOTE: After FIM procedure accomplishment it is necessary to do the inspection of sensing element. 2 Deactivate the sensing elements according to wiring modification. If the sensing elements were deactivated, it will be necessary to activate them according to PART VIII of this Bulletin. NOTE: In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). (b) If there are no short or open conditions (False) on CMC, do as follows: 1 Get access to the sensing elements, by removing the applicable access and floor panels; SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 3 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 6 2 Perform the inspection on the active sensing elements according to section 3. ACCOMPLISHMENT INSTRUCTIONS in order to detect the possible sensing element failures; 3 Replace the failed sensing elements with a new one with the same PN or with a PN presented in the Aircraft Illustrated Parts Catalog (AIPC), according to the applicable AMM task. To get access to the work areas, it is necessary to remove/open panels according to Table Affected PN x Access Panel for PART II. PART III INSPECTION AND REPLACEMENT OF THE ODS SENSINGELEMENTS OF LH WING BLEED SYSTEM (SLAT 1 AREA) Applicable to: 1.A. SB EFFECTIVITY The modification presented in PART III of this bulletin consists of inspecting the sensing elements of the Overheat Detection System (ODS) related to LH wing bleed system, installed at slat 1 area. This PART presents the following actions: (1) Check if there is any short or open condition (True) in the LH bleed system. (a) If there are any short or open conditions on CMC, two actions are possible to be done: 1 Do the troubleshooting according to FIM (Fault Isolation Manual) and perform the sensing elements inspection, or; NOTE: After FIM procedure accomplishment it is necessary to do the inspection of the sensing element. 2 Deactivate the sensing elements according to wiring modification. If the sensing elements were deactivated, it will be necessary to activate them according to PART VIII of this Bulletin. NOTE: In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). (b) If there are no short or open conditions (False) on CMC, do as follows: 1 Get access to the sensing elements, by removing the applicable access and floor panels; 2 Perform the inspection on the active sensing elements according to section 3. ACCOMPLISHMENT INSTRUCTIONS in order to detect the possible sensing element failures; 3 Replace the failed sensing elements with a new one with the same PN or with a PN presented in the Aircraft Illustrated Parts Catalog (AIPC), according to the applicable AMM task. To get access to the work areas, it is necessary to remove/open panels according to Table Affected PN x Access Panel for PART III. PART IV INSPECTION AND REPLACEMENT OF THE ODS SENSINGELEMENTS OF RH WING BLEED SYSTEM (SLAT 1 AREA) Applicable to: 1.A. SB EFFECTIVITY SERVICE BULLETIN SB190-36-0027 Page 4 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 7 The modification presented in PART IV of this bulletin consists of the inspection of the sensing elements of the Overheat Detection System (ODS) related to RH wing bleed system, installed at slat 1 area. This PART presents the following actions: (1) Check if there is any short or open condition (True) in the RH bleed system loops. (a) If there are any short or open conditions on CMC, two actions are possible to be done: 1 Do the troubleshooting according to FIM (Fault Isolation Manual) and perform the sensing elements inspection described in step (b), or; NOTE: After FIM procedure accomplishment it is necessary to do the inspection of the sensing element. 2 Deactivate the sensing elements according to wiring modification. If the sensing elements were deactivated, it will be necessary to activate them according to PART VIII of this Bulletin. NOTE: In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). (b) If there are no short or open conditions (False) on CMC, do as follows: 1 Get access to the sensing elements, by removing the applicable access and floor panels; 2 Perform the inspection on the active sensing elements according to section 3. ACCOMPLISHMENT INSTRUCTIONS in order to detect the possible sensing element failures; 3 Replace the failed sensing elements with a new one with the same PN or with a PN presented in the Aircraft Illustrated Parts Catalog (AIPC), according to the applicable AMM task. To get access to the work areas, it is necessary to remove/open panels according to Table Affected PN x Access Panel for PART IV. PART V INSPECTION AND REPLACEMENT OF THE ODS SENSINGELEMENTS OF LH WING BLEED SYSTEM (EXCEPT SLAT 1 AREA) Applicable to: 1.A. SB EFFECTIVITY The modification presented in PART V of this bulletin consists of the inspection of the sensing elements of the Overheat Detection System (ODS) related to LH wing bleed system installed at central fuselage II and pylon. This PART presents the following actions: (1) Check if there is any short or open condition (True) in the LH wing bleed system. (a) If there are any short or open conditions on CMC, two actions are possible to be done: 1 Do the troubleshooting according to FIM (Fault Isolation Manual) and perform the sensing elements inspection, or; NOTE: After FIM procedure accomplishment it is necessary to do the inspection of the sensing element. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 5 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 8 2 Deactivate the sensing elements according to wiring modification. If the sensing elements were deactivated, it will be necessary to activate them according to PART VIII of this Bulletin. NOTE: In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). (b) If there are no short or open conditions (False) on CMC, do as follows: 1 Get access to the sensing elements, by removing the applicable access and floor panels; 2 Perform the inspection on the active sensing elements according to section 3. ACCOMPLISHMENT INSTRUCTIONS in order to detect the possible sensing element failures; 3 Replace the failed sensing elements with a new one with the same PN or with a PN presented in the Aircraft Illustrated Parts Catalog (AIPC), according to the applicable AMM task. To get access to the work areas, it is necessary to remove/open panels according to Table Affected PN x Access Panel for PART V. PART VI INSPECTION AND REPLACEMENT OF THE ODS SENSING ELEMENTS OF RH WING BLEED SYSTEM (EXCEPT SLAT 1 AREA) AND TRIM PRESSURE DUCTS (IF APPLICABLE) Applicable to: 1.A. SB EFFECTIVITY The modification presented in PART VI of this bulletin consists of the inspection of the sensing elements of the Overheat Detection System (ODS) related to RH wing bleed system installed at central fuselage II and pylon and trim pressure ducts areas. NOTE: The trim pressure ducts are not installed in all aircraft mentioned in section 1.A. SB EFFECTIVITY since is an optional system related to Trim Air Modulating System (Air conditioning - Dual Zone). This PART presents the following actions: (1) Check if there is any short or open condition (True) in the RH bleed system and Trim pressure ducts. (a) If there are any short or open conditions on CMC, two actions are possible to be done: 1 Do the troubleshooting according to FIM (Fault Isolation Manual) and perform the sensing elements inspection described in step (b), or; NOTE: After FIM procedure accomplishment it is necessary to do the inspection of the sensing element. 2 Deactivate the sensing elements according to wiring modification. If the sensing elements were deactivated, it will be necessary to activate them according to PART VIII of this Bulletin. NOTE: In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). (b) If there are no short or open conditions (False) on CMC, do as follows: SERVICE BULLETIN SB190-36-0027 Page 6 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 9 1 Get access to the sensing elements, by removing the applicable access and floor panels; 2 Perform the inspection on the active sensing elements according to section 3. ACCOMPLISHMENT INSTRUCTIONS in order to detect the possible sensing element failures; 3 Replace the failed sensing elements with a new one with the same PN or with a PN presented in the Aircraft Illustrated Parts Catalog (AIPC), according to the applicable AMM task. To get access to the work areas, it is necessary to remove/open panels according to Table Affected PN x Access Panel for PART VI. PART VII INSPECTION AND REPLACEMENT OF THE APU BLEED LINE ODS SENSING ELEMENTS LOCATED AT NON-PRESSURIZED AREAS, AND CARGO-COMPARTMENT Applicable to: 1.A. SB EFFECTIVITY The modification presented in PART VII of this bulletin consists of inspecting the sensing elements of the Overheat Detection System (ODS) related to APU bleed line located at non-pressurized areas, and cargo-compartment. NOTE: Inspection of ODS related APU bleed line, installed at mid-bay, aft-bay and stub is presented in PART I of this bulletin This PART presents the following actions: (1) Check if there is any short or open condition (True) in the APU bleed line located at non- pressurized area, and cargo compartment. (a) If there are any short or open conditions on CMC, two actions are possible to be done: 1 Do the troubleshooting according to FIM (Fault Isolation Manual) and perform the sensing elements inspection described in step (b), or; NOTE: After FIM procedure accomplishment it is necessary to do the inspection of the sensing element. 2 Deactivate the sensing elements according to wiring modification. If the sensing elements were deactivated, it will be necessary to activate them according to PART VIII of this Bulletin. NOTE: In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). (b) If there are no short or open conditions (False) on CMC, do as follows: 1 Get access to the sensing elements, by removing the applicable access and floor panels; 2 Perform the inspection on the active sensing elements according to section 3. ACCOMPLISHMENT INSTRUCTIONS in order to detect the possible sensing element failures; 3 Replace the failed sensing elements with a new one with the same PN or with a PN presented in the Aircraft Illustrated Parts Catalog (AIPC), according to the applicable AMM task. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 7 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 10 To get access to the work areas, it is necessary to remove/open panels according to Table Affected PN x Access Panel for PART VII. PART VIII RE-ACTIVATION OF DEACTIVATED SENSING ELEMENTS FROM PARTs I THRU VII AND INSPECT THE ACTIVATED ODS SENSING ELEMENTS Applicable to: 1.A. SB EFFECTIVITY The modification presented in PART VIII of this bulletin consists of the reactivation of the sensing elements of the Overheat Detection System (ODS) related to any of the ODS sensing elements deactivated on PART I thru PART VII. This PART presents the following actions: (1) Re-activate the sensing element according to the electrical wiring modification; (2) Open the CMC screen (OVERHEAT DETECTION PARAMETERS) and verify if there is any short or open condition (True) in the related loops. (a) If there are any short or open conditions on CMC, do as follows: 1 Do the troubleshooting of the sensing element according to FIM (Fault Isolation Manual); NOTE: After FIM procedure accomplishment it is necessary to do the inspection of the sensing element. (b) If there are no short or open conditions (False) on CMC, do as follows: 1 Get access to the sensing elements, by removing the applicable access and floor panels according to the respective table; 2 Perform the inspection on the active sensing elements according to section 3. ACCOMPLISHMENT INSTRUCTIONS in order to detect the possible sensing element failures; 3 Replace the failed sensing elements with a new one with the same PN or with a PN presented in the Aircraft Illustrated Parts Catalog (AIPC), according to the applicable AMM task. NOTE: The modification presented in this bulletin does not affect Fatigue Critical Structure (FCS). E. COMPLIANCE 1) SB CATEGORY Category 01: MANDATORY 2) SB ACCOMPLISHMENT – APPLICABLE TO PART I, PART II, PART III, PART IV, PART V, PART VI, and PART VII This Bulletin must be accomplished in the next 10,000 FH or 48 months from the original issue date of this bulletin, whichever occurs first. – APPLICABLE TO PART VIII SERVICE BULLETIN SB190-36-0027 Page 8 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 11 Embraer recommends the accomplishment of PART VIII of this SB at the next suitable maintenance opportunity where manpower and facilities are available. The PART VIII is applicable if a Overheat Detection System (ODS) channel was deactivated according to any of the previous parts. 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 Service Bulletin 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. If the applicable AD does not make any reference to the RC (Required for Compliance) and/or RC Exempt, then the RC and RC Exempt concept is not valid for this Service Bulletin, and an AMOC is necessary in case of any deviation from the Service Bulletin steps. F. APPROVAL The inspection mentioned in this Service Bulletin does not affect the type design previously 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. (1) APPLICABLE TO PART I – Access opening: 2.0 man-hours. – Inspection: 0.75 man-hours. – Modification: See the Note. – Access closure: 2.5 man-hours. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 9 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 12 – Test: See the Note. NOTE: – The items Modification and Test will change according to the quantity of sensing elements that presents failure. – The estimated time to items Access opening and Access Closure may be affected if seats are removed and the PART VII of this bulletin is accomplished at the same time. (2) APPLICABLE TO PART II – Access opening: 1.5 man-hours. – Inspection: 0.5 man-hours. – Modification: See the Note. – Access closure: 2.0 man-hours. – Test: See the Note. NOTE: The items Modification and Test will change according to the quantity of sensing elements that presents failure. (3) APPLICABLE TO PART III – Access opening: 1.0 man-hour. – Inspection: 0.25 man-hours. – Modification: See the Note. – Access closure: 1.0 man-hour. – Test: See the Note. NOTE: The items Modification and Test will change according to the quantity of sensing elements that presents failure. (4) APPLICABLE TO PART IV – Access opening: 1.0 man-hour. – Inspection: 0.25 man-hours. – Modification: See the Note. – Access closure: 1.0 man-hour. – Test: See the Note. NOTE: The items Modification and Test will change according to the quantity of sensing elements that presents failure. (5) APPLICABLE TO PART V – Access opening: 0.25 man-hours. – Inspection: 0.25 man-hours. – Modification: See the Note. SERVICE BULLETIN SB190-36-0027 Page 10 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 13 – Access closure: 0.5 man-hours. – Test: See the Note. NOTE: – The items Modification and Test will change according to the quantity of sensing elements that presents failure. – The estimated time to items Access opening and Access Closure may be affected if Wing-to-Fuselage Fairing (WFF) is removed and the PART VI of this bulletin is accomplished at the same time. (6) APPLICABLE TO PART VI – Access opening: 1.0 man-hour. – Inspection: 1.0 man-hour. – Modification: See the Notes. – Access closure: 1.0 man-hour. – Test: See the Notes. NOTE: – The items Modification and Test will change according to the quantity of sensing elements that presents failure. – The estimated time to items Access opening and Access Closure may be affected if Wing-to-Fuselage Fairing (WFF) is removed and the PART V of this bulletin is accomplished at the same time. (7) APPLICABLE TO PART VII – Access opening: 1.0 man-hour. – Inspection: 1.0 man-hour. – Modification: See the Notes. – Access closure: 1.0 man-hour. – Test: See the Notes. NOTE: – The items Modification and Test will change according to the quantity of sensing elements that presents failure. – The estimated time to items Access opening and Access Closure may be affected if seats are removed and the PART I of this bulletin is accomplished at the same time. (8) APPLICABLE TO PART VIII – Access opening: 1.5 man-hours. – Inspection: 1.0 man-hour. – Modification: 1.0 man-hours. – Access closure: 1.0 man-hour. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 11 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 14 – Test: See note. NOTE: – The time for electrical modification and test is estimated for one loop only. If more loops were modified, this value must be multiplied accordingly. – The estimated time to items Access opening and Access Closure may be affected if Wing-to-Fuselage Fairing (WFF) is removed. – After reactivating the ODS channel, it is required to do the inspection again relating to applicable PART, according to the loop. H. WEIGHT AND BALANCE None. I. SOFTWARE ACCOMPLISHMENT SUMMARY None. J. REFERENCES AIPC 190/( ) Aircraft Illustrated Parts Catalog - 30-11-08 - ICE AND RAIN PROTECTION. AIPC 190/( ) Aircraft Illustrated Parts Catalog - 36-21-02 and 36-22-01 - PNEUMATIC. AMM 190/( ) Aircraft Maintenance Manual PART II - 06-41-00, 06-43-00, 06-44-00,06-46-00, 06-48-00, and 06-49-00 - DIMENSIONS AND AREAS. AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARDPRACTICES-AIRFRAME. AMM 190/( ) Aircraft Maintenance Manual PART II - 24-42-02 - ELECTRICAL POWER. AMM 190/( ) Aircraft Maintenance Manual PART II - 25-21-11 and 25-24-01 -EQUIPMENT/FURNISHINGS. AMM 190/( ) Aircraft Maintenance Manual PART II - 30-11-08 - ICE AND RAINPROTECTION. AMM 190/( ) Aircraft Maintenance Manual PART II - 36-21-02 and 36-22-01 -PNEUMATIC. AMM 190/( ) Aircraft Maintenance Manual PART II - 45-45-00 - CENTRALMAINTENANCE SYSTEM. AMM 190/( ) Aircraft Maintenance Manual PART II - 57-49-20 - WINGS. FIM 190/( ) Fault Isolation Manual - 30-11-00 - ICE AND RAIN PROTECTION. FIM 190/( ) Fault Isolation Manual - 36-21-00 and 36-22-00 - PNEUMATIC. SWPM 190/(1590) Standard Wiring Practices Manual - 20-01-02, 20-41-10, and 20-50-10 -STANDARD PRACTICES-AIRFRAME. WM 190/( ) Wiring Manual - 24-61-50 - ELECTRICAL POWER. SERVICE BULLETIN SB190-36-0027 Page 12 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 15 K. OTHER PUBLICATIONS AFFECTED None. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 13 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 16 2. MATERIAL INFORMATION A. MATERIAL - PRICE AND AVAILABILITY (1) MATERIAL AVAILABLE FROM EMBRAER None. (2) MATERIAL AVAILABLE FROM OTHER VENDORS Refer to section 2.D. MATERIAL NECESSARY FOR EACH SPARE. B. INDUSTRY SUPPORT INFORMATION (1) To return the failed sensing elements and to order the new sensing elements contact Collins Aerospace at address mentioned below: – Collins Aerospace – 4200 Airport Dr – Wilson, NC 27896 – Attn: CFD NOE Return (2) For Labor Reimbursement: – The instructions for warranty claims can be found at https://portal.rockwellcollins.com/web/ support-self-service/warranty – Operators can also forward claims for labor reimbursement to the e-mail: kiddewarranty@collins.com. 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. (1) TOP KITS AND KITS None. (2) MATERIAL TO BE PROCURED (a) Parts None. (b) Consumable Materials None. (c) Kit Updating SERVICE BULLETIN SB190-36-0027 Page 14 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 17 None. D. MATERIAL NECESSARY FOR EACH SPARE 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. (1) MATERIAL TO BE PROCURED (a) Parts The parts below should be procured from the manufacturer, as indicated in the associated Note and will be available at no charge to the operator. NOTE: – The quantity of parts that will be requested will change according to failure occurrences. – If is necessary to replace a sensing element, and the same PN is not available or even no longer furnished by supplier, check the interchangeability in AIPC, and place the order, as applicable. – All alternate or interchangeable Part Numbers of sensing elements listed on the AIPC are affected as well. – Collins Aerospace will replace any sensing elements that fails inspection on a free of charge basis until April 30, 2025. Refer to SB190-36-0027 on the purchase order. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. APPLICABLE TO PART I NEW PN DESCRIPTION OLD PN QTY DISP/Notes 04-90005-180A Sensing Element 04-90005-180A 02 7 / [1] 04-90005-116A 04-90005-116A 02 7 / [1] 04-90005-145A 04-90005-145A 01 7 / [1] 04-90005-147A 04-90005-147A 01 7 / [1] [1] To disconnect the connector use heat-shrinkable PN RNF-100 1/8-9 and tie-down strap PN MS3367-7-9. APPLICABLE TO PART II NEW PN DESCRIPTION OLD PN QTY DISP/Notes 04-90005-015A Sensing Element 04-90005-015A 04 7 / [1] [1] To disconnect the connector use heat-shrinkable PN RNF-100 1/8-9 and tie-down strap PN MS3367-7-9. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 15 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 18 APPLICABLE TO PART III NEW PN DESCRIPTION OLD PN QTY DISP/Notes 04-90005-085A Sensing Element 04-90005-085A 04 7 / [1] [1] To disconnect the connector use heat-shrinkable PN RNF-100 1/8-9 and tie-down strap PN MS3367-7-9. APPLICABLE TO PART IV NEW PN DESCRIPTION OLD PN QTY DISP/Notes 04-90005-087A Sensing Element 04-90005-087A 02 7 / [1] 04-90005-086A 04-90005-086A 01 7 / [1] 04-90005-084A 04-90005-084A 01 7 / [1] [1] To disconnect the connector use heat-shrinkable PN RNF-100 1/8-9 and tie-down strap PN MS3367-7-9. APPLICABLE TO PART V NEW PN DESCRIPTION OLD PN QTY DISP/Notes 04-90005-163A Sensing Element 04-90005-163A 02 7 / [1] 04-90005-094A 04-90005-094A 01 7 / [1] 04-90005-096A 04-90005-096A 01 7 / [1] 04-90005-105C 04-90005-105C 02 7 / [1] [1] To disconnect the connector use heat-shrinkable PN RNF-100 1/8-9 and tie-down strap PN MS3367-7-9. APPLICABLE TO PART VI NEW PN DESCRIPTION OLD PN QTY DISP/Notes 04-90005-155A Sensing Element 04-90005-155A 02 7 / [1] 04-90005-096A 04-90005-096A 01 7 / [1] 04-90005-099A 04-90005-099A 01 7 / [1] 04-90005-109C 04-90005-109C 02 7 / [1] 04-90005-130A / [2] 04-90005-130A 01 7 / [1] 04-90005-136A / [2] 04-90005-136A 01 7 / [1] 04-90005-099A / [2] 04-90005-099A 02 7 / [1] [1] To disconnect the connector use heat-shrinkable PN RNF-100 1/8-9 and tie-down strap PN MS3367-7-9. [2] This Part Number is just applicable for aircraft equiped with TRIM. SERVICE BULLETIN SB190-36-0027 Page 16 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 19 APPLICABLE TO PART VII NEW PN DESCRIPTION OLD PN QTY DISP/Notes 04-90005-146A Sensing Element 04-90005-146A 02 7 / [1] 04-90005-172A 04-90005-172A 02 7 / [1] 04-90005-122A 04-90005-122A 02 7 / [1] 04-90005-125A 04-90005-125A 02 7 / [1] 04-90005-059A 04-90005-059A 02 7 / [1] [1] To disconnect the connector use heat-shrinkable PN RNF-100 1/8-9 and tie-down strap PN MS3367-7-9. APPLICABLE TO PART VIII NEW PN DESCRIPTION OLD PN QTY DISP/Notes 617 300 PIN 617 300 AR 7 / [1] [1] The Pin PN 617 300 is necessary if the existing pin is damaged. DISPOSITION: 7 = Replace with part bearing same PN QUANTITY: AR = As Required E. REIDENTIFIED PARTS None. F. TOOLING - PRICE AND AVAILABILITY To do the inspection in the sensing lines, it is necessary that operators manufacturer a device (Heat Protection Shield) to use in conjunction with the Heat-Gun. This device is to protect the adjacent areas of the inspection and also to concentrate the heating in the sensing lines. The heat protection shield is made of stainless steel, with a thickness approximately 1 mm (0.04 in). Use the dimensions in Figure 1. NOTE: You can use equivalent material to manufacture the heat protection shield. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 17 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 20 3. ACCOMPLISHMENT INSTRUCTIONS NOTE: 1) Obey all of the WARNINGS and CAUTIONS included in the mentioned manuals and procedures. 2) 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. 3) For the purpose of this Service Bulletin, a Detailed Inspection (DET) is: “An intensive examination of a specific item, installation or assembly to detect damage, failure or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirrors, magnifying lenses, etc. may be necessary. Surface cleaning and elaborate access procedures may be required.” 4) 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 Service Bulletin 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. If the applicable AD does not make any reference to the RC (Required for Compliance) and/or RC Exempt, then the RC and RC Exempt concept is not valid for this Service Bulletin, and an AMOC is necessary in case of any deviation from the Service Bulletin steps. 5) 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. 6) If it is necessary to remove more parts for access, you can remove those parts. If you can get access without removing identified parts, it is not necessary to remove all of the identified parts. 7) This Service Bulletin is divided into 08 PARTS. The SB PARTS division allows their independent accomplishment. 8) The PART VIII is just applicable if the sensing element was deactivated according to any of the previous parts. The steps below outline the general accomplishment instructions. The detailed sequence is included in the respective figure, when necessary. 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. Connect the external AC power supply to the aircraft (AMM TASK 24-42-02-860-801-A/200 - Connection of the external AC power supply to the aircraft - Aircraft/System Configuration). C. After the cockpit screens are ON, wait for 5 minutes. D. On the EICAS display, make sure that no LEAK messages are displayed, as follows: SERVICE BULLETIN SB190-36-0027 Page 18 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 21 – BLEED 1 LEAK – BLEED 2 LEAK – PACK 2 LEAK – BLEED APU LEAK – A-I WING 1 LEAK – A-I WING 2 LEAK E. On the AIR COND/PNEUMATIC and ICE PROTECTION control panel, set the pushbuttons as follows: (Refer to Figure 3.) – BLEED 1 Pushbutton: OUT (OFF) – BLEED 2 Pushbutton: OUT (OFF) – BLEED APU Pushbutton: OUT (OFF) – PACK 1 Pushbutton: OUT (OFF) – PACK 2 Pushbutton: OUT (OFF) – WING Pushbutton: OUT (OFF) – XBLEED: OUT (OFF) F. Calibrate the heat-gun temperature with the heat protection shield device and a thermocouple, as shown in Figure 4, as follows: (1) For the part numbers ending with "A", the heat gun needs to be adjusted to 171 (-0, +17) °C. Examples: PN 04-90005-145A, 04-90005-015A; (2) For the part numbers ending with "C", the heat gun needs to be adjusted to 200 (-16, +0) °C. Examples: PN 04-90005-042C, 04-90005-041C; G. PART I – INSPECTION AND REPLACEMENT OF APU BLEED LINE ODS SENSING ELEMENTS LOCATED AT MID-BAY, AFT-BAY AND STUB. (1) On the CMC, use the sequence that follows to get access to the BLEED ODS NVM READ/ RESET TEST (AMM TASK 45-45-00-970-805-A/200 - Access to the Test Pages on the CMC): – 36 - PNEUMATIC – 11 - BLEED AIR SYSTEM 1 – BLEED ODS NVM READ/RESET TEST Go to Page 2 of the BLEED ODS NVM READ/RESET TEST, to see the REAL TIME DATA. [RC] On the CMC, on the BLEED ODS NVM READ/RESET TEST page, make sure that the TRUE indication does not show in any of the messages below in the APU loops: – [RC] OVERHEAT CONDITION – [RC] SHORT CONDITION – [RC] OPEN CONDITION – [RC] Make sure that the EVENT LOCATION shows 0.00 (ZERO) for APU loops SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 19 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 22 (a) Do a check of the conditions above in the loops of PART I of this service bulletin, and do as follows: 1 [RC] If there is any of the conditions above (TRUE) on CMC, two actions are possible: a [RC] Do the troubleshooting according to FIM (Fault Isolation Manual) and proceed with sensing elements inspection according to step 2 below to make sure that the sensing elements are operational, or; b [RC] If there is no sensor element available, do the deactivation of the sensing elements according to the wiring modification, and proceed with sensing elements inspection according to step 2 below to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. NOTE: – Refer to SWPM 20-50-10 - Electrical Connectors Assembly - Maintenance Practices, SWPM 20-41-10 - Wire Termination Code - Description and SWPM 20-01-02 - Identification of Wires and Cables - Description. – In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). – If only one of the channels was deactivated, the aircraft can be operated without restrictions because the overheat condition is monitored by the channel that is operational. – If the channel was deactivated, it will be necessary to activate them according to PART VIII of this Bulletin at the next suitable maintenance opportunity where manpower and facilities are available. – The Figure 13 is applicable for Channel 1 of aircraft equipped with Single Zone (no Trim valves); – The Figure 14 is applicable for Channel 2 of aircraft equipped with Single Zone (no Trim valves); – The Figure 15 is applicable for Channel 1 of aircraft equipped with Dual Zone (Trim valves installed); – The Figure 16 is applicable for Channel 2 of aircraft equipped with Dual Zone (Trim valves installed); 2 If there are no short or open conditions (False) on CMC, or if one of the channels was deactivated, do the inspection of the sensing element, as follows: a Make sure that the BLEED APU LEAK message is not active on EICAS display. If the message is active, go to FIM TASK 36-22-00-810-802-A to do the applicable troubleshooting. b Make sure that the BLEED APU Pushbutton is OFF in the AIR COND/ PNEUMATIC control panel. c Open the applicable panels to get the access the affected Overheat Detection System (ODS) sensing elements. SERVICE BULLETIN SB190-36-0027 Page 20 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 23 Affected PN x Access Panel for PART I Monitored Area Affected PN Access panel AMM TASK APU DUCT – CF II 04-90005-180 A /[1] 241FLF 147AL 241HLF AMM MPP 06-46-00/100 - FLOOR ACCESS DOORS AND PANELS - COMPONENT LOCATION AMM MPP 06-49-00/100 - CARGO- COMPARTMENT ACCESS DOORS AND PANELS - COMPONENT LOCATION 04-90005-116 A / [1] 241FLF 147AL 241HLF AMM MPP 06-46-00/100 - FLOOR ACCESS DOORS AND PANELS - COMPONENT LOCATION AMM MPP 06-49-00/100 - CARGO- COMPARTMENT ACCESS DOORS AND PANELS - COMPONENT LOCATION [1] Remove the applicable passenger seats (AMM TASK 25-21-11-000-801-A/400 - Passen- ger Seats - Removal), and passenger-cabin floor finish (AMM TASK 25-24-01-000-801- A/400 - Passenger-Cabin Floor Finish - Removal). Install passenger-cabin floor finish (AMM TASK 25-24-01-400-801-A/400 - Passenger-Cabin Floor Finish - Installation) and passenger seat (AMM TASK 25-21-11-400-801-A/400 - Passenger Seats - Installation) af- ter the inspection and replacement of the sensing element is complete. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 21 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 24 Affected PN x Access Panel for PART I (Continued) Monitored Area Affected PN Access panel AMM TASK APU DUCT – CF III 04-90005-145 A 252AZ 151BZ 151CLW 151BLW 151ALW AMM MPP 06-48-00/100 - PASSENGER- CABIN ACCESS PANELS - COMPONENT LOCATION AMM MPP 06-49-00/100 - CARGO- COMPARTMENT ACCESS DOORS AND PANELS - COMPONENT LOCATION 04-90005-147 A 252AZ 151BZ 151CLW 151BLW 151ALW AMM MPP 06-48-00/100 - PASSENGER- CABIN ACCESS PANELS - COMPONENT LOCATION AMM MPP 06-49-00/100 - CARGO- COMPARTMENT ACCESS DOORS AND PANELS - COMPONENT LOCATION d [RC] Do the Detailed Inspection (DET) of the sensing element. Refer to Figure 2 and Figure 5. (2) Inspection of the sensing element results: (a) [RC] After the time specified in the inspection procedure of the sensing elements described in Figure 2, if the BLEED APU LEAK message comes into view on EICAS display, it means that the sensing element is operating correctly, and no further action is required. (b) [RC] If the BLEED APU LEAK message DOES NOT come into view on EICAS display at any of the tested positions, do as follows: 1 [RC] Identify in the Central Maintenance Computer (CMC) what is the shorted channel (SHORT CONDITION=TRUE) during the inspection; 2 [RC] Replace the sensor associated to the OTHER CHANNEL (i.e. SHORT CONDITION=FALSE), using the replacement instructions described in the AMM MPP 36-22-01/400 - APU LINE LEAK DETECTORS - REMOVAL/INSTALLATION and AIPC 36-22-01 - APU LINE LEAK DETECTORS. SERVICE BULLETIN SB190-36-0027 Page 22 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 25 – [RC] If both channels present SHORT CONDITION=FALSE during the test, then both sensors need to be replaced; – [RC] If there is no sensor element available for replacement, do the deactivation of the loop according to the wiring modification and proceed with the sensing elements inspection according to Figure 2 to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. – If additional information is necessary to identify which sensor is related to each channel, refer to Aircraft Illustrated Parts Catalog (AIPC) and WM 24-61-50 - DC POWER DISTRIBUTION SYSTEM. 3 [RC] After you replace the sensor element, do the Detailed Inspection (DET) again according to the inspection procedure in Figure 2, to make sure that the channels are operational. a Send the removed sensing element to supplier. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. H. PART II – INSPECTION AND REPLACEMENT OF THE ODS SENSING ELEMENTS OF LH AND RH WING ANTI-ICE SUPPLY DUCTS (1) On the CMC, use the sequence that follows to get access to the BLEED ODS NVM READ/ RESET TEST (AMM TASK 45-45-00-970-805-A/200 - Access to the Test Pages on the CMC): – 36 - PNEUMATIC – 11 - BLEED AIR SYSTEM 1 – BLEED ODS NVM READ/RESET TEST Go to Page 2 of the BLEED ODS NVM READ/RESET TEST, to see the REAL TIME DATA. [RC] On the CMC, on the BLEED ODS NVM READ/RESET TEST page, make sure that the TRUE indication does not show in any of the messages below in the loops of the LH and RH anti- ice supply ducts: – [RC] OVERHEAT CONDITION – [RC] SHORT CONDITION – [RC] OPEN CONDITION – [RC] Make sure that the EVENT LOCATION shows 0.00 (ZERO) for LH AND RH ANTI-ICE SUPPLY DUCTS loops (a) Do a check of the conditions above in the loops of PART II of this service bulletin, and do as follows: 1 [RC] If there is any of the conditions above (TRUE) on CMC, two actions are possible: a [RC] Do the troubleshooting according to FIM (Fault Isolation Manual) and proceed with sensing elements inspection according to step 2 below to make sure that the sensing elements are operational, or; SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 23 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 26 b [RC] If there is no sensor element available, do the deactivation of the sensing elements according to the wiring modification, and proceed with sensing elements inspection according to step 2 below to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. NOTE: – Refer to SWPM 20-50-10 - Electrical Connectors Assembly - Maintenance Practices, SWPM 20-41-10 - Wire Termination Code - Description and SWPM 20-01-02 - Identification of Wires and Cables - Description. – In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). – If only one of the channels was deactivated, the aircraft can be operated without restrictions because the overheat condition is monitored by the channel that is operational. – If the channel was deactivated, it will be necessary to activate them according to PART VIII of this Bulletin at the next suitable maintenance opportunity where manpower and facilities are available. – The Figure 13 is applicable for Channel 1 of aircraft equipped with Single Zone (no Trim valves); – The Figure 14 is applicable for Channel 2 of aircraft equipped with Single Zone (no Trim valves); – The Figure 15 is applicable for Channel 1 of aircraft equipped with Dual Zone (Trim valves installed); – The Figure 16 is applicable for Channel 2 of aircraft equipped with Dual Zone (Trim valves installed); 2 If there are no short or open conditions (False) on CMC, or if one of the channels was deactivated, do the inspection of the sensing element, as follows: a Make sure that the A-I WING 1 LEAK and A-I WING 2 LEAK message are not active on EICAS display. If any of the messages is active, go to FIM TASK 30-11-00-810-818-A for A-I WING 1 LEAK or FIM TASK 30-11-00-810-819-A for A-I WING 2 LEAK to do the applicable troubleshooting. b On the ICE PROTECTION control panel, set the WING pushbutton to OUT (OFF). c Open the applicable panels to get the access the affected Overheat Detection System (ODS) sensing elements. SERVICE BULLETIN SB190-36-0027 Page 24 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 27 Affected PN x Access Panel for PART II Monitored Area Affected PN Access panel AMM TASK LH ANTI- ICE SUPPLY DUCTS 04-90005-015 A 516AB 516QT 515DT AMM MPP 06-44-00/100 - WING ACCESS DOORS AND PANELS - COMPONENT LOCATION RH ANTI- ICE SUPPLY DUCTS 616AB 616QT 615DT d [RC] Do the Detailed Inspection (DET) of sensing element. Refer to Figure 2 and Figure 6. (2) Inspection of the sensing element results: (a) [RC] After the time specified in the inspection procedure of the sensing elements described in Figure 2, if the A-I WING 1 LEAK or A-I WING 2 LEAK message comes into view on EICAS display, it means that the sensing element is operating correctly, and no further action is required. (b) [RC] If the A-I WING 1 LEAK or A-I WING 2 LEAK message DOES NOT come into view on EICAS display at any of the tested position, do as follows: 1 [RC] Identify in the Central Maintenance Computer (CMC) what is the shorted channel (SHORT CONDITION=TRUE) during the inspection; 2 [RC] Replace the sensor associated to the OTHER CHANNEL (i.e. SHORT CONDITION=FALSE), using the replacement instructions described in the AMM MPP 30-11-08/400 - ANTI-ICING LEAK DETECTORS - REMOVAL/INSTALLATION and AIPC 30-11-08 - ANTI-ICING LEAK DETECTORS. – [RC] If both channels present SHORT CONDITION=FALSE during the test, then both sensors need to be replaced; – [RC] If there is no sensor element available for replacement, do the deactivation of the loop according to the wiring modification and proceed with the sensing elements inspection according to Figure 2 to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. – If additional information is necessary to identify which sensor is related to each channel, refer to Aircraft Illustrated Parts Catalog (AIPC) and WM 24-61-50 - DC POWER DISTRIBUTION SYSTEM. 3 [RC] After you replace the sensor element, do the Detailed Inspection (DET) again according to the inspection procedure in Figure 2, to make sure that the channels are operational. a Send the removed sensing element to supplier. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. I. PART III – INSPECTION AND REPLACEMENT OF THE ODS SENSING ELEMENTS OF LH WING BLEED SYSTEM (SLAT 1 AREA) SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 25 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 28 (1) On the CMC, use the sequence that follows to get access to the BLEED ODS NVM READ/ RESET TEST (AMM TASK 45-45-00-970-805-A/200 - Access to the Test Pages on the CMC): – 36 - PNEUMATIC – 11 - BLEED AIR SYSTEM 1 – BLEED ODS NVM READ/RESET TEST Go to Page 2 of the BLEED ODS NVM READ/RESET TEST, to see the REAL TIME DATA. [RC] On the CMC, on the BLEED ODS NVM READ/RESET TEST page, make sure that the TRUE indication does not show in any of the messages below in the LH WING BLEED 1 loops: – [RC] OVERHEAT CONDITION – [RC] SHORT CONDITION – [RC] OPEN CONDITION – [RC] Make sure that the EVENT LOCATION shows 0.00 (ZERO) for LH WING BLEED 1 loops (a) Do a check of the conditions above in the loops of PART III of this service bulletin, and do as follows: 1 [RC] If there is any of the conditions above (TRUE) on CMC, two actions are possible: a [RC] Do the troubleshooting according to FIM (Fault Isolation Manual) and proceed with sensing elements inspection according to step 2 below to make sure that the sensing elements are operational, or; SERVICE BULLETIN SB190-36-0027 Page 26 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 29 b [RC] If there is no sensor element available, do the deactivation of the sensing elements according to the wiring modification, and proceed with sensing elements inspection according to step 2 below to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. NOTE: – Refer to SWPM 20-50-10 - Electrical Connectors Assembly - Maintenance Practices, SWPM 20-41-10 - Wire Termination Code - Description and SWPM 20-01-02 - Identification of Wires and Cables - Description. – In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). – If only one of the channels was deactivated, the aircraft can be operated without restrictions because the overheat condition is monitored by the channel that is operational. – If the channel was deactivated, it will be necessary to activate them according to PART VIII of this Bulletin at the next suitable maintenance opportunity where manpower and facilities are available. – The Figure 13 is applicable for Channel 1 of aircraft equipped with Single Zone (no Trim valves); – The Figure 14 is applicable for Channel 2 of aircraft equipped with Single Zone (no Trim valves); – The Figure 15 is applicable for Channel 1 of aircraft equipped with Dual Zone (Trim valves installed); – The Figure 16 is applicable for Channel 2 of aircraft equipped with Dual Zone (Trim valves installed); 2 If there are no short or open conditions (False) on CMC, or if one of the channels was deactivated, do the inspection of the sensing element, as follows: a Make sure that the BLEED 1 LEAK message is not active on EICAS display. If the message is active, go to FIM TASK 36-21-00-810-803-A to do the applicable troubleshooting. b Make sure that the BLEED APU and XBLEED Pushbuttons are set to OFF in the AIR COND/PNEUMATIC control panel. c Open the applicable panels to get the access the affected Overheat Detection System (ODS) sensing elements. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 27 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 30 Affected PN x Access Panel for PART III Monitored Area Affected PN Access panel AMM TASK LH BLEED SYSTEM DUCTS 04-90005-085 A [1] 515BB 515AB 419CT 515DT AMM MPP 06-41-00/100 - FUSELAGE ACCESS DOORS AND PANELS - COMPONENT LOCATION AMM MPP 06-43-00/100 - POWERPLANT AND PYLON ACCESS DOORS AND PANELS - COMPONENT LOCATION AMM MPP 06-44-00/100 - WING ACCESS DOORS AND PANELS - COMPONENT LOCATION [1] If necessary, remove Wing-Root Landing-Light Lens Fairing (AMM TASK 57-49-20-000-801-A/400 - Wing-Root Landing-Light Lens Fairing - Removal). Install Wing-Root Landing-Light Lens (AMM TASK 57-49-20-400-801-A/400 - Wing-Root Land- ing-Light-Lens Fairing - Installation) after the inspection and replacement of the sensing element is complete. d [RC] Do the Detailed Inspection (DET) of sensing element. Refer to Figure 2 and Figure 7. (2) Inspection of the sensing element results: (a) [RC] After the time specified in the inspection procedure of the sensing elements described in Figure 2, if the BLEED 1 LEAK message comes into view on EICAS display, it means that the sensing element is operating correctly, and no further action is required. (b) [RC] If the BLEED 1 LEAK message DOES NOT come into view on EICAS display at any of the tested position, do as follows: 1 [RC] Identify in the Central Maintenance Computer (CMC) what is the shorted channel (SHORT CONDITION=TRUE) during the inspection; 2 [RC] Replace the sensor associated to the OTHER CHANNEL (i.e. SHORT CONDITION=FALSE), using the replacement instructions described in the AMM MPP 36-21-02/400 - BLEED LINES LEAK DETECTORS - REMOVAL/INSTALLATION and AIPC 36-21-02 - BLEED LINES LEAK DETECTORS. – [RC] If both channels present SHORT CONDITION=FALSE during the test, then both sensors need to be replaced; – [RC] If there is no sensor element available for replacement, do the deactivation of the loop according to the wiring modification and proceed with the sensing elements inspection according to Figure 2 to make sure that the active loop is SERVICE BULLETIN SB190-36-0027 Page 28 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 31 operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. – If additional information is necessary to identify which sensor is related to each channel, refer to Aircraft Illustrated Parts Catalog (AIPC) and WM 24-61-50 - DC POWER DISTRIBUTION SYSTEM. 3 [RC] After you replace the sensor element, do the Detailed Inspection (DET) again according to the inspection procedure in Figure 2, to make sure that the channels are operational. a Send the removed sensing element to supplier. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. J. PART IV – INSPECTION AND REPLACEMENT OF THE ODS SENSING ELEMENTS OF RH WING BLEED SYSTEM (SLAT 1 AREA) (1) On the CMC, use the sequence that follows to get access to the BLEED ODS NVM READ/ RESET TEST (AMM TASK 45-45-00-970-805-A/200 - Access to the Test Pages on the CMC): – 36 - PNEUMATIC – 11 - BLEED AIR SYSTEM 1 – BLEED ODS NVM READ/RESET TEST Go to Page 2 of the BLEED ODS NVM READ/RESET TEST, to see the REAL TIME DATA. [RC] On the CMC, on the BLEED ODS NVM READ/RESET TEST page, make sure that the TRUE indication does not show in any of the messages below in the RH WING BLEED loops: – [RC] OVERHEAT CONDITION – [RC] SHORT CONDITION – [RC] OPEN CONDITION – [RC] Make sure that the EVENT LOCATION shows 0.00 (ZERO) for RH WING BLEED loops (a) Do a check of the conditions above in the loops of PART IV of this service bulletin, and do as follows: 1 [RC] If there is any of the conditions above (TRUE) on CMC, two actions are possible: a [RC] Do the troubleshooting according to FIM (Fault Isolation Manual) and proceed with sensing elements inspection according to step 2 below to make sure that the sensing elements are operational, or; SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 29 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 32 b [RC] If there is no sensor element available, do the deactivation of the sensing elements according to the wiring modification, and proceed with sensing elements inspection according to step 2 below to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. NOTE: – Refer to SWPM 20-50-10 - Electrical Connectors Assembly - Maintenance Practices, SWPM 20-41-10 - Wire Termination Code - Description and SWPM 20-01-02 - Identification of Wires and Cables - Description. – In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). – If only one of the channels was deactivated, the aircraft can be operated without restrictions because the overheat condition is monitored by the channel that is operational. – If the channel was deactivated, it will be necessary to activate them according to PART VIII of this Bulletin at the next suitable maintenance opportunity where manpower and facilities are available. – The Figure 13 is applicable for Channel 1 of aircraft equipped with Single Zone (no Trim valves); – The Figure 14 is applicable for Channel 2 of aircraft equipped with Single Zone (no Trim valves); – The Figure 15 is applicable for Channel 1 of aircraft equipped with Dual Zone (Trim valves installed); – The Figure 16 is applicable for Channel 2 of aircraft equipped with Dual Zone (Trim valves installed); 2 If there are no short or open conditions (False) on CMC, or if one of the channels was deactivated, do the inspection of the sensing element, as follows: a Make sure that the BLEED 2 LEAK message is not active on EICAS display. If the message is active, go to FIM TASK 36-21-00-810-804-A to do the applicable troubleshooting. b Make sure that the BLEED APU and XBLEED Pushbuttons are set to OFF in the AIR COND/PNEUMATIC control panel. c Open the applicable panels to get the access the affected Overheat Detection System (ODS) sensing elements. SERVICE BULLETIN SB190-36-0027 Page 30 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 33 Affected PN x Access Panel for PART IV Monitored Area Affected PN Access panel AMM TASK RH BLEED SYSTEM DUCTS 04-90005-084 A [1] 615AB 615BB 429PL 429CT 615DT AMM MPP 06-41-00/100 - FUSELAGE ACCESS DOORS AND PANELS - COMPONENT LOCATION AMM MPP 06-43-00/100 - POWERPLANT AND PYLON ACCESS DOORS AND PANELS - COMPONENT LOCATION AMM MPP 06-44-00/100 - WING ACCESS DOORS AND PANELS - COMPONENT LOCATION 04-90005-086 A [1] 04-90005-087 A[1] [1] If necessary, remove Wing-Root Landing-Light Lens Fairing (AMM TASK 57-49-20-000-801-A/400 - Wing-Root Landing-Light Lens Fairing - Removal). Install Wing- Root Landing-Light Lens (AMM TASK 57-49-20-400-801-A/400 - Wing-Root Landing- Light-Lens Fairing - Installation) after the inspection and replacement of the sensing ele- ment is complete. d [RC] Do the Detailed Inspection (DET) of sensing element. Refer to Figure 2 and Figure 8. (2) Inspection of the sensing element results: (a) [RC] After the time specified in the inspection procedure of the sensing elements described in Figure 2, if the BLEED 2 LEAK message comes into view on EICAS display, it means that the sensing element is operating correctly, and no further action is required. (b) [RC] If the BLEED 2 LEAK message DOES NOT come into view on EICAS display at any of the tested positions, do as follows: 1 [RC] Identify in the Central Maintenance Computer (CMC) what is the shorted channel (SHORT CONDITION=TRUE) during the inspection; 2 [RC] Replace the sensor associated to the OTHER CHANNEL (i.e. SHORT CONDITION=FALSE), using the replacement instructions described in the AMM MPP 36-21-02/400 - BLEED LINES LEAK DETECTORS - REMOVAL/INSTALLATION and AIPC 36-21-02 - BLEED LINES LEAK DETECTORS. – [RC] If both channels present SHORT CONDITION=FALSE during the test, then both sensors need to be replaced; – [RC] If there is no sensor element available for replacement, do the deactivation of the loop according to the wiring modification and proceed with the sensing elements inspection according to Figure 2 to make sure that the active loop is SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 31 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 34 operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. – If additional information is necessary to identify which sensor is related to each channel, refer to Aircraft Illustrated Parts Catalog (AIPC) and WM 24-61-50 - DC POWER DISTRIBUTION SYSTEM. 3 [RC] After you replace the sensor element, do the Detailed Inspection (DET) again according to the inspection procedure in Figure 2, to make sure that the channels are operational. a Send the removed sensing element to supplier. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. K. PART V – INSPECTION AND REPLACEMENT OF THE ODS SENSING ELEMENTS OF LH BLEED SYSTEM (EXCEPT SLAT 1 AREA) (1) On the CMC, use the sequence that follows to get access to the BLEED ODS NVM READ/ RESET TEST (AMM TASK 45-45-00-970-805-A/200 - Access to the Test Pages on the CMC): – 36 - PNEUMATIC – 11 - BLEED AIR SYSTEM 1 – BLEED ODS NVM READ/RESET TEST Go to Page 2 of the BLEED ODS NVM READ/RESET TEST, to see the REAL TIME DATA. [RC] On the CMC, on the BLEED ODS NVM READ/RESET TEST page, make sure that the TRUE indication does not show in any of the messages below in the LH BLEED loops: – [RC] OVERHEAT CONDITION – [RC] SHORT CONDITION – [RC] OPEN CONDITION – [RC] Make sure that the EVENT LOCATION shows 0.00 (ZERO) for LH BLEED loops (a) Do a check of the conditions above in the loops of PART V of this service bulletin, and do as follows: 1 [RC] If there is any of the conditions above (TRUE) on CMC, two actions are possible: a [RC] Do the troubleshooting according to FIM (Fault Isolation Manual) and proceed with sensing elements inspection according to step 2 below to make sure that the sensing elements are operational, or; SERVICE BULLETIN SB190-36-0027 Page 32 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 35 b [RC] If there is no sensor element available, do the deactivation of the sensing elements according to the wiring modification, and proceed with sensing elements inspection according to step 2 below to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. NOTE: – Refer to SWPM 20-50-10 - Electrical Connectors Assembly - Maintenance Practices, SWPM 20-41-10 - Wire Termination Code - Description and SWPM 20-01-02 - Identification of Wires and Cables - Description. – In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). – If only one of the channels was deactivated, the aircraft can be operated without restrictions because the overheat condition is monitored by the channel that is operational. – If the channel was deactivated, it will be necessary to activate them according to PART VIII of this Bulletin at the next suitable maintenance opportunity where manpower and facilities are available. – The Figure 13 is applicable for Channel 1 of aircraft equipped with Single Zone (no Trim valves); – The Figure 14 is applicable for Channel 2 of aircraft equipped with Single Zone (no Trim valves); – The Figure 15 is applicable for Channel 1 of aircraft equipped with Dual Zone (Trim valves installed); – The Figure 16 is applicable for Channel 2 of aircraft equipped with Dual Zone (Trim valves installed); 2 If there are no short or open conditions (False) on CMC, or if one of the channels was deactivated, do the inspection of the sensing element, as follows: a Make sure that the BLEED 1 LEAK message is not active on EICAS display. If the message is active, go to FIM TASK 36-21-00-810-803-A to do the applicable troubleshooting. b Make sure that the BLEED APU and XBLEED Pushbuttons are set to OFF in the AIR COND/PNEUMATIC control panel. c Open the applicable panels to get the access the affected Overheat Detection System (ODS) sensing elements. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 33 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 36 Affected PN x Access Panel for PART V Monitored Area Affected PN Access panel AMM TASK LH BLEED SYSTEM DUCTS 04-90005-105 C 419GR 419JR 419NR 419ADR 419AT AMM MPP 06-43-00/100 - POWERPLANT AND PYLON ACCESS DOORS AND PANELS - COMPONENT LOCATION AMM MPP 06-44-00/100 - WING ACCESS DOORS AND PANELS - COMPONENT LOCATION 04-90005-163 A 191EL 191CL 191BL 192AL AMM MPP 06-41-00/100 - FUSELAGE ACCESS DOORS AND PANELS - COMPONENT LOCATION 04-90005-094 A 04-90005-096 A d [RC] Do the Detailed Inspection (DET) of sensing element. Refer to Figure 2, Figure 9. (2) Inspection of the sensing element results: (a) [RC] After the time specified in the inspection procedure of the sensing elements described in Figure 2, if the BLEED 1 LEAK message comes into view on EICAS display, it means that the sensing element is operating correctly, and no further action is required. (b) [RC] If the BLEED 1 LEAK message DOES NOT come into view on EICAS display at any of the tested positions, do as follows: 1 [RC] Identify in the Central Maintenance Computer (CMC) what is the shorted channel (SHORT CONDITION=TRUE) during the inspection; 2 [RC] Replace the sensor associated to the OTHER CHANNEL (i.e. SHORT CONDITION=FALSE), using the replacement instructions described in the AMM MPP 36-21-02/400 - BLEED LINES LEAK DETECTORS - REMOVAL/INSTALLATION and AIPC 36-21-02 - BLEED LINES LEAK DETECTORS. – [RC] If both channels present SHORT CONDITION=FALSE during the test, then both sensors need to be replaced; – [RC] If there is no sensor element available for replacement, do the deactivation of the loop according to the wiring modification and proceed with the sensing elements inspection according to Figure 2 to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. SERVICE BULLETIN SB190-36-0027 Page 34 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 37 – If additional information is necessary to identify which sensor is related to each channel, refer to Aircraft Illustrated Parts Catalog (AIPC) and WM 24-61-50 - DC POWER DISTRIBUTION SYSTEM. 3 [RC] After you replace the sensor element, do the Detailed Inspection (DET) again according to the inspection procedure in Figure 2, to make sure that the channels are operational. a Send the removed sensing element to supplier. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. L. PART VI – INSPECTION AND REPLACEMENT OF THE ODS SENSING ELEMENTS OF RH WING BLEED SYSTEM (EXCEPT SLAT 1 AREA) AND TRIM PRESSURE DUCTS (IF APPLICABLE) (1) On the CMC, use the sequence that follows to get access to the BLEED ODS NVM READ/ RESET TEST (AMM TASK 45-45-00-970-805-A/200 - Access to the Test Pages on the CMC): – 36 - PNEUMATIC – 11 - BLEED AIR SYSTEM 1 – BLEED ODS NVM READ/RESET TEST Go to Page 2 of the BLEED ODS NVM READ/RESET TEST, to see the REAL TIME DATA. [RC] On the CMC, on the BLEED ODS NVM READ/RESET TEST page, make sure that the TRUE indication does not show in any of the messages below in the RH BLEED and TRIM (if applicable) loops: – [RC] OVERHEAT CONDITION – [RC] SHORT CONDITION – [RC] OPEN CONDITION – [RC] Make sure that the EVENT LOCATION shows 0.00 (ZERO) for RH BLEED and TRIM (if applicable) loops (a) Do a check of the conditions above in the loops of PART VI of this service bulletin, and do as follows: 1 [RC] If there is any of the conditions above (TRUE) on CMC, two actions are possible to be done: a [RC] Do the troubleshooting according to FIM (Fault Isolation Manual) and proceed with sensing elements inspection according to step 2 below to make sure that the sensing elements are operational, or; SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 35 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 38 b [RC] If there is no sensor element available, do the deactivation of the sensing elements according to the wiring modification, and proceed with sensing elements inspection according to step 2 below to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. NOTE: – Refer to SWPM 20-50-10 - Electrical Connectors Assembly - Maintenance Practices, SWPM 20-41-10 - Wire Termination Code - Description and SWPM 20-01-02 - Identification of Wires and Cables - Description. – In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). – If only one of the channels was deactivated, the aircraft can be operated without restrictions because the overheat condition is monitored by the channel that is operational. – If the channel was deactivated, it will be necessary to activate them according to PART VIII of this Bulletin at the next suitable maintenance opportunity where manpower and facilities are available. – The Figure 13 is applicable for Channel 1 of aircraft equipped with Single Zone (no Trim valves); – The Figure 14 is applicable for Channel 2 of aircraft equipped with Single Zone (no Trim valves); – The Figure 15 is applicable for Channel 1 of aircraft equipped with Dual Zone (Trim valves installed); – The Figure 16 is applicable for Channel 2 of aircraft equipped with Dual Zone (Trim valves installed); 2 If there are no short or open conditions (False) on CMC, or if one of the channels was deactivated, do the inspection of the sensing element, as follows: a Make sure that the BLEED 2 LEAK and PACK 2 LEAK messages are not active on EICAS display. If any of the message is active, go to FIM TASK 36-21-00-810-804-A or FIM TASK 21-62-00-810-825-A (IF APPLICABLE) to do the applicable troubleshooting. b Make sure that the below pushbutton are set as follows in the AIR COND/ PNEUMATIC control panel: – BLEED 2 Pushbutton: OUT (OFF) – PACK 1 Pushbutton: OUT (OFF) – PACK 2 Pushbutton: OUT (OFF) – BLEED APU Pushbutton: OUT (OFF) – XBLEED Pushbutton: OUT (OFF) c Open the applicable panels to get the access the affected Overheat Detection System (ODS) sensing elements. SERVICE BULLETIN SB190-36-0027 Page 36 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 39 Affected PN x Access Panel for PART VI Monitored Area Affected PN Access panel AMM TASK TRIM PRESSUR E DUCTS 04-90005-130 A 141AZ 142AZ AMM MPP 06-49-00/100 - CARGO- COMPARTMENT ACCESS DOORS AND PANELS - COMPONENT LOCATION 04-90005-099 A 04-90005-136 A RH BLEED SYSTEM DUCTS 04-90005-109 C 429ADL 429ML 429HL 429FL 429AT AMM MPP 06-43-00/100 - POWERPLANT AND PYLON ACCESS DOORS AND PANELS - COMPONENT LOCATION 04-90005-155 A 191AR 191BL 191CL 191EL AMM MPP 06-41-00/100 - FUSELAGE ACCESS DOORS AND PANELS - COMPONENT LOCATION 04-90005-099 A 04-90005-096 A d [RC] Do the Detailed Inspection (DET) of sensing element. Refer to Figure 2 and Figure 10. (2) Inspection of sensing element results: (a) [RC] After the time specified in the inspection procedure of the sensing elements described in Figure 2, if the BLEED 2 LEAK or PACK 2 LEAK message comes into view on EICAS display, it means that the sensing element is operating correctly, and no further action is required. (b) [RC] If the BLEED 2 LEAK or PACK 2 LEAK message DOES NOT come into view on EICAS display at any of the tested positions, do as follows: 1 [RC] Identify in the Central Maintenance Computer (CMC) what is the shorted channel (SHORT CONDITION=TRUE) during the inspection; 2 [RC] Replace the sensor associated to the OTHER CHANNEL (i.e. SHORT CONDITION=FALSE), using the replacement instructions described in the AMM MPP 36-21-02/400 - BLEED LINES LEAK DETECTORS - REMOVAL/INSTALLATION or AMM 21-62-03/400 - TRIM-AIR-SYSTEM LEAK DETECTORS - REMOVAL/ INSTALLATION (IF APPLICABLE) and AIPC 36-21-02 - BLEED LINES LEAK DETECTORS or AIPC 21-62-03 - TRIM AIR LEAK DETECTORS (IF APPLICABLE). – [RC] If both channels present SHORT CONDITION=FALSE during the test, then both sensors need to be replaced; – [RC] If there is no sensor element available for replacement, do the deactivation of the loop according to the wiring modification and proceed with the sensing SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 37 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 40 elements inspection according to Figure 2 to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. – If additional information is necessary to identify which sensor is related to each channel, refer to Aircraft Illustrated Parts Catalog (AIPC) and WM 24-61-50 - DC POWER DISTRIBUTION SYSTEM. 3 [RC] After you replace the sensor element, do the Detailed Inspection (DET) again according to the inspection procedure in Figure 2, to make sure that the channels are operational. a Send the removed sensing element to supplier. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. M. PART VII – INSPECTION AND REPLACEMENT OF THE APU BLEED LINE ODS SENSING ELEMENTS LOCATED AT NON-PRESSURIZED AREAS, AND CARGO-COMPARTMENT (1) On the CMC, use the sequence that follows to get access to the BLEED ODS NVM READ/ RESET TEST (AMM TASK 45-45-00-970-805-A/200 - Access to the Test Pages on the CMC): – 36 - PNEUMATIC – 11 - BLEED AIR SYSTEM 1 – BLEED ODS NVM READ/RESET TEST Go to Page 2 of the BLEED ODS NVM READ/RESET TEST, to see the REAL TIME DATA. [RC] On the CMC, on the BLEED ODS NVM READ/RESET TEST page, make sure that the TRUE indication does not show in any of the messages below in the APU loops: – [RC] OVERHEAT CONDITION – [RC] SHORT CONDITION – [RC] OPEN CONDITION – [RC] Make sure that the EVENT LOCATION shows 0.00 (ZERO) for APU loops (a) Do a check of the conditions above in the loops of PART VII of this service bulletin, and do as follows: 1 [RC] If there is any of the conditions above (TRUE) on CMC, two actions are possible: a [RC] Do the troubleshooting according to FIM (Fault Isolation Manual) and proceed with sensing elements inspection according to step 2 below to make sure that the sensing elements are operational, or; SERVICE BULLETIN SB190-36-0027 Page 38 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 41 b [RC] If there is no sensor element available, do the deactivation of the sensing elements according to the wiring modification, and proceed with sensing elements inspection according to step 2 below to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. NOTE: – Refer to SWPM 20-50-10 - Electrical Connectors Assembly - Maintenance Practices, SWPM 20-41-10 - Wire Termination Code - Description and SWPM 20-01-02 - Identification of Wires and Cables - Description. – In case of two inoperative channels from the same loop, the airplane must be dispatched according to the applicable restrictions of the Operator's approved Minimum Equipment List (MEL). – If only one of the channels was deactivated, the aircraft can be operated without restrictions because the overheat condition is monitored by the channel that is operational. – If the channel was deactivated, it will be necessary to activate them according to PART VIII of this Bulletin at the next suitable maintenance opportunity where manpower and facilities are available. – The Figure 13 is applicable for Channel 1 of aircraft equipped with Single Zone (no Trim valves); – The Figure 14 is applicable for Channel 2 of aircraft equipped with Single Zone (no Trim valves); – The Figure 15 is applicable for Channel 1 of aircraft equipped with Dual Zone (Trim valves installed); – The Figure 16 is applicable for Channel 2 of aircraft equipped with Dual Zone (Trim valves installed); 2 If there are no short or open conditions (False) on CMC, or if one of the channels was deactivated, do the inspection of the sensing element, as follows: a Make sure that the BLEED APU LEAK message is not active on EICAS display. If the message is active, go to FIM TASK 36-22-00-810-802-A to do the applicable troubleshooting. b Make sure that the Bleed APU pushbutton is set to OUT (OFF) in the AIR COND/PNEUMATIC control panel. c Open the applicable panels to get the access the affected Overheat Detection System (ODS) sensing elements. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 39 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 42 Affected PN x Access Panel for PART VII Monitored Area Affected PN Access panel AMM TASK APU DUCT – CF III 04-90005-146 A 04-90005-122 A 04-90005-125 A 04-90005-059 A 151CLW 151BLW 151ALW 148ARW 148BRW 241FLF 147BLW 147ALW 241HLF AMM MPP 06-49-00/100 - CARGO- COMPARTMENT ACCESS DOORS AND PANELS - COMPONENT LOCATION APU DUCT – REAR FUSELAGE 04-90005-172 A 314BR AMM MPP 06-41-00/100 - FUSELAGE ACCESS DOORS AND PANELS - COMPONENT LOCATION d [RC] Do the Detailed Inspection (DET) of the sensing element. Refer to Figure 2 and Figure 11. (2) Inspection of the sensing element results: (a) [RC] After the time specified in the inspection procedure of the sensing elements described in Figure 2, if the BLEED APU LEAK message comes into view on EICAS display, it means that the sensing element is operating correctly, and no further action is required. (b) [RC] If the BLEED APU LEAK message DOES NOT come into view on EICAS display at any of the tested positions, do as follows: 1 [RC] Identify in the Central Maintenance Computer (CMC) what is the shorted channel (SHORT CONDITION=TRUE) during the inspection; 2 [RC] Replace the sensor associated to the OTHER CHANNEL (i.e. SHORT CONDITION=FALSE), using the replacement instructions described in the AMM MPP 36-22-01/400 - APU LINE LEAK DETECTORS - REMOVAL/INSTALLATION and AIPC 36-22-01 - APU LINE LEAK DETECTORS. – [RC] If both channels present SHORT CONDITION=FALSE during the test, then both sensors need to be replaced; – [RC] If there is no sensor element available for replacement, do the deactivation of the loop according to the wiring modification and proceed with the sensing elements inspection according to Figure 2 to make sure that the active loop is operational. Refer to Figure 12 for connectors location, and Figure 13, Figure 14, Figure 15 and Figure 16 (as applicable) for electrical diagrams modification. – If additional information is necessary to identify which sensor is related to each channel, refer to Aircraft Illustrated Parts Catalog (AIPC) and WM 24-61-50 - DC POWER DISTRIBUTION SYSTEM. 3 [RC] After you replace the sensor element, do the Detailed Inspection (DET) again according to the inspection procedure in Figure 2, to make sure that the channels are operational. SERVICE BULLETIN SB190-36-0027 Page 40 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 43 a Send the removed sensing element to supplier. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. N. PART VIII - RE-ACTIVATION OF DEACTIVATED SENSING ELEMENTS FROM PARTs I THRU VII AND INSPECT THE ACTIVATED ODS SENSING ELEMENTS (1) [RC] Do the activation of the applicable sensing element according to electrical diagrams modification. Refer to Figure 12 for connector location and Figure 17, Figure 18, Figure 19 and Figure 20. NOTE: Refer to SWPM 20-50-10 - Electrical Connectors Assembly - Maintenance Practices, SWPM 20-41-10 - Wire Termination Code - Description and SWPM 20-01-02 - Identification of Wires and Cables - Description. (2) On the CMC, use the sequence that follows to get access to the BLEED ODS NVM READ/ RESET TEST (AMM TASK 45-45-00-970-805-A/200 - Access to the Test Pages on the CMC): – 36 - PNEUMATIC – 11 - BLEED AIR SYSTEM 1 – BLEED ODS NVM READ/RESET TEST Go to Page 2 of the BLEED ODS NVM READ/RESET TEST, to see the REAL TIME DATA. [RC] On the CMC, on the BLEED ODS NVM READ/RESET TEST page, make sure that the TRUE indication does not show in any of the messages below in the loops: – [RC] OVERHEAT CONDITION – [RC] SHORT CONDITION – [RC] OPEN CONDITION – [RC] Make sure that the EVENT LOCATION shows 0.00 (ZERO) for loops (a) If there is any short or open conditions on CMC, do as follows: 1 [RC] Do the troubleshooting of the sensing element according to FIM (Fault Isolation Manual) and proceed with sensing elements inspection according to the applicable sensing element (PARTs I thru VII) to make sure that the loops are operational, or; (b) If there are no short or open conditions (False) on CMC, do as follows: 1 Get access to the sensing elements, by removing the applicable access and floor panels according to the respective table (PARTs I thru VII); 2 [RC] Perform the inspection on the active sensing elements according to related procedure of PARTs I thru VII in order to detect the possible sensing failures; 3 [RC] If the inspection failed, replace the failed sensing elements with a new one with the same PN according to Aircraft Illustrated Parts Catalog (AIPC) and the applicable AMM task. a Send the removed sensing element to supplier. Refer to 2.B. INDUSTRY SUPPORT INFORMATION. 4 [RC] If a sensor was replaced, do the inspection of the sensing elements again, as described in the inspection procedure in Figure 2. O. Put the aircraft back to a serviceable condition. SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 41 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 44 P. Write the accomplishment of PART I and/or PART II and/or PART III and/or PART IV and/or PART V and/or PART VI and/or PART VII and/or PART VIII of this bulletin in the applicable documents. NOTE: Please use the online SB evaluation form available on the FlyEmbraer portal ( http:// www.flyembraer.com). Go to "Maintenance > TechPubs > Select > aircraft > Tools > 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 SB190-36-0027 Page 42 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 45 FIGURE 1 - HEAT PROTECTION SHIELD MANUFACTURING AND USING (Sheet 1 of 3) 1. To manufacturer the Heat Protection shield it is necessary the material described in section 2.F. TOOLING - PRICE AND AVAILABILITY SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 43 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 46 FIGURE 1 - HEAT PROTECTION SHIELD MANUFACTURING AND USING (Sheet 2 of 3) EM170SB360470B.IDR 70.00 mm (2.75 in) RADIUS APPROX. 19.10 mm (0.75 in) SENSING ELEMENTS HEAT PROTECTION SHIELD HEAT GUN OUTLET 25.40 mm (1.00 in) HEAT PROTECTION SHIELD SENSING ELEMENTS HEAT GUN OUTLET 35.60 TO 40.60 mm (1.4 TO 1.6 in) 25.40 mm (1.0 in) AIRFLOW STAINLESS STEEL THICKNESS APROX: 1.0 mm (0.04 in) 19.10 mm (0.75in) (APPROX.) NOTE: DIMENSION IN mm (in) 25.40 mm (1.00 in) 25.40 mm (1.0 in) SERVICE BULLETIN SB190-36-0027 Page 44 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 47 FIGURE 1 - HEAT PROTECTION SHIELD MANUFACTURING AND USING (Sheet 3 of 3) EM170SB360472A.IDR HEAT PROTECTION SHIELD HEAT-GUN EXTENTION ASSEMBLY EXAMPLE SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 45 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 48 FIGURE 2 - BLEED SENSING ELEMENTS INSPECTION (Sheet 1 of 3) WARNING: OBEY THE SAFETY PRECAUTIONS WHEN YOU DO TASKS WITH A HEATING GUN. IF YOU USE AN INCORRECT HEATING GUN NEAR FLAMMABLE MATERIAL OR FUEL VENT, EXPLOSION CAN OCCUR. 1. To do the inspection of the sensing elements, it is necessary to use the Heat Protection Shield manufactured with the dimensions of Figure 1. 2. For Reference: The Detail A shows the Heat Protection Shield using on the Pylon region and the another detail shows the Heat Protection Shield using at general other areas. 3. For each SB Part (loop) follow the sequence below to do the inspection of the sensing elements: (a) Position the heat protection shield on the sensing element to be inspected and equally warm up both sensors with calibrated heat gun. (b) Warm up both sensors for at least 120 seconds or until the related EICAS message shows on the EICAS display (whichever occurs first). 1 Trim ODS lines (PNs 04 90005 136A, 04 90005 130A, and 04 90005 099A), warm up the sensors for 210 seconds instead of 120 seconds. (c) If the nozzle of heat gun diameter is smaller than 1 inch (25.4 mm), then increase the inspection time (warm up) by 30 seconds and move the hot air gently side- to-side to increase the heat transfer area to the sensor. SERVICE BULLETIN SB190-36-0027 Page 46 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 49 FIGURE 2 - BLEED SENSING ELEMENTS INSPECTION (Sheet 2 of 3) EM170SB360473A.IDR PYLON (REF.) HEAT PROTECTION SHIELD A ZONES 419/429 515/615 A SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 47 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 50 FIGURE 2 - BLEED SENSING ELEMENTS INSPECTION (Sheet 3 of 3) EM170SB360474A.IDR SENSING ELEMENT SENSING ELEMENT HEAT PROTECTION SHIELD HEAT GUN SERVICE BULLETIN SB190-36-0027 Page 48 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 51 FIGURE 3 - AIR COND / PNEUMATIC PANEL (Sheet 1 of 1) EM170SB360471A.IDR AIR COND / PNEUMATIC PANEL A A ANTI-ICE PROTECTION CONTROL PANEL AIR COND / PNEUMATIC CKPT RECIRC CABINPAX C H WING 1 START 1 PACK 1 ATTND C H PACK 2 XBLEED CONN GND BLEED 1 BLEED APU BLEED 2 START 2 WING 2 1 MODE AUTO TEST OFF WINGENG ENGINE 2 2 WINDSHIELD HEATING ICE PROTECTION ENGINE 1 WING ON SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 49 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 52 FIGURE 4 - HEAT GUN CALIBRATION (Sheet 1 of 1) EM170SB360475A.IDR HEAT PROTECTION SHIELD HEAT GUN THERMOCOUPLE SERVICE BULLETIN SB190-36-0027 Page 50 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 53 FIGURE 5 - ODS LOCATION - APPLICABLE TO PART I (Sheet 1 of 2) EM170SB360596A.IDR A ODS LOOP JOINT ODS LOOP END 1 3 (APPLICABLE TO EMBRAER 190 AND EMBRAER 195 AIRCRAFT) IF THIS CONNECTOR IS BETWEEN THE SENSOR AND THE PIGTAIL, THE TEST POINT POSITION MUST BE IN THE SENSOR, AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. IF THIS CONNECTOR IS BETWEEN 2 SENSORS, THE TWO SENSORS MUST BE TESTED AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. THIS TEST POINT CORRESPONDS TO APPROXIMATELY 50% OF THE SENSORS LENGTH. TEST TWO SENSORS IN THIS POSITION.1 2 3 ZONES 141/142/145 147/148 A FR 61FR 60FR 58FR 57 SPAR III SPAR II ODS LOOP JOINT 1 3 SPAR I 1 ODS PN 04-90005-180A 1 1 3 1 1 ODS PN 04-90005-116A 1 1 2 1 2 (PART I) SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 51 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 54 FIGURE 5 - ODS LOCATION - APPLICABLE TO PART I (Sheet 2 of 2) EM170SB360594B.IDR ZONES 151 152 A IF THIS CONNECTOR IS BETWEEN THE SENSOR AND THE PIGTAIL, THE TEST POINT POSITION MUST BE IN THE SENSOR, AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. IF THIS CONNECTOR IS BETWEEN 2 SENSORS, THE TWO SENSORS MUST BE TESTED AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. THIS TEST POINT CORRESPONDS TO APPROXIMATELY 50% OF THE SENSORS LENGTH. TEST TWO SENSORS IN THIS POSITION. 2 3 ODS PN 04-90005-145A AND PN 04-90005-147A IS APPLICABLE TO PART I.4 1 FR 86 FR 89 ODS LOOP JOINT ODS LOOP JOINT THE NEXT FRAME (FR91) IS THE PRESSURE BULKHEAD 1 1 3 1 1 2 1 3 1 A (PART I) ODS PN 04-90005-147A 4 ODS PN 04-90005-145A 4 (APPLICABLE TO EMBRAER 190 AND EMBRAER 195 AIRCRAFT) SERVICE BULLETIN SB190-36-0027 Page 52 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 55 FIGURE 6 - ODS LOCATION - APPLICABLE TO PART II (Sheet 1 of 2) EM170SB360598A.IDR IF THIS CONNECTOR IS BETWEEN THE SENSOR AND THE PIGTAIL, THE TEST POINT POSITION MUST BE IN THE SENSOR, AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. IF THIS CONNECTOR IS BETWEEN 2 SENSORS, THE TWO SENSORS MUST BE TESTED AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. THIS TEST POINT CORRESPONDS TO APPROXIMATELY 50% OF THE SENSORS LENGTH. TEST TWO SENSORS IN THIS POSITION.1 2 3 A (APPLICABLE TO EMBRAER 190 AND EMRAER 195 AIRCRAFT) (PART II) A ZONE 515 RIB 13 RIB 12 RIB 11 SPAR I (LH) BLEED (REF.) PYLON (REF.) 3 13 1 ODS PN 04-90005-015A SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 53 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 56 FIGURE 6 - ODS LOCATION - APPLICABLE TO PART II (Sheet 2 of 2) EM170SB360599A.IDR IF THIS CONNECTOR IS BETWEEN THE SENSOR AND THE PIGTAIL, THE TEST POINT POSITION MUST BE IN THE SENSOR, AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. IF THIS CONNECTOR IS BETWEEN 2 SENSORS, THE TWO SENSORS MUST BE TESTED AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. THIS TEST POINT CORRESPONDS TO APPROXIMATELY 50% OF THE SENSORS LENGTH. TEST TWO SENSORS IN THIS POSITION.1 2 3 RIB 13 RIB 12 RIB 11 SPAR I (RH) BLEED (REF.) PYLON (REF.) 3 1 ODS PN 04-90005-015A A ZONE 615 3 1 A (PART II) (APPLICABLE TO EMBRAER 190 AND EMRAER 195 AIRCRAFT) SERVICE BULLETIN SB190-36-0027 Page 54 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 57 FIGURE 7 - ODS LOCATION - APPLICABLE TO PART III (Sheet 1 of 1) EM170SB360600B.IDR IF THIS CONNECTOR IS BETWEEN THE SENSOR AND THE PIGTAIL, THE TEST POINT POSITION MUST BE IN THE SENSOR, AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. IF THIS CONNECTOR IS BETWEEN 2 SENSORS, THE TWO SENSORS MUST BE TESTED AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. THIS TEST POINT CORRESPONDS TO APPROXIMATELY 50% OF THE SENSORS LENGTH. TEST TWO SENSORS IN THIS POSITION.1 2 3 BLEED SYSTEM - LH WING SPAR I (LH) ODS PN 04-90005-085A LEAK DETECTION FAIRING BLEED SYSTEM ODS LOOP JOINT RIB 03 ODS LOOP JOINT A A ZONES 419 515 (PART III) RIB 06 RIB 09 1 1 3 1 2 1 1 1 1 2 BLEED FAIRING SYSTEM ODS PN 04-90005-085A BLEED PYLON SYSTEM ANTI-ICE SYSTEM 1 3 ODS LOOP JOINT 1 3 SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 55 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 58 FIGURE 8 - ODS LOCATION - APPLICABLE TO PART IV (Sheet 1 of 1) EM170SB360601B.IDR IF THIS CONNECTOR IS BETWEEN THE SENSOR AND THE PIGTAIL, THE TEST POINT POSITION MUST BE IN THE SENSOR, AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. IF THIS CONNECTOR IS BETWEEN 2 SENSORS, THE TWO SENSORS MUST BE TESTED AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. THIS TEST POINT CORRESPONDS TO APPROXIMATELY 50% OF THE SENSORS LENGTH. TEST TWO SENSORS IN THIS POSITION. 2 3 A ZONES 429 615 ODS PN 04-90005-087A ODS LOOP JOINT A BLEED SYSTEM - RH WING (PART IV) 1 1 1 3 1 2 BLEED PYLON SYSTEM ANTI-ICE SYSTEM BLEED FAIRING SYSTEM RIB 09 RIB 06 RIB 03 1 2 1 1 ODS LOOP JOINT 1 3 SPAR I (RH) 1 ODS LOOP JOINT 1 3 LEAK DETECTION FAIRING BLEED SYSTEM ODS PN 04-90005-086A ODS PN 04-90005-084A SERVICE BULLETIN SB190-36-0027 Page 56 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 59 FIGURE 9 - ODS LOCATION - APPLICABLE TO PART V (Sheet 1 of 2) EM170SB360602B.IDR IF THIS CONNECTOR IS BETWEEN THE SENSOR AND THE PIGTAIL, THE TEST POINT POSITION MUST BE IN THE SENSOR, AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. IF THIS CONNECTOR IS BETWEEN 2 SENSORS, THE TWO SENSORS MUST BE TESTED AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. THIS TEST POINT CORRESPONDS TO APPROXIMATELY 50% OF THE SENSORS LENGTH. TEST TWO SENSORS IN THIS POSITION.1 2 3 LEFT PYLON STRUCTURE A ZONES 419 515 1 1 2 ODS PN 04-90005-105C HARNESS W507 1 ODS LOOP JOINT 1 3 ODS LOOP JOINT 1 3 HARNESS W506 HARNESS W507 1 BLEED WING SYSTEM TM SERVO LINE-NACELLE VALVES PRECOOLER SYSTEM SEGREG WALL A (PART V) (APPLICABLE TO EMBRAER 190 AND EMBRAER 195 AIRCRAFT) SERVICE BULLETIN Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 SB190-36-0027 Page 57 of 118 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 ### Page 60 FIGURE 9 - ODS LOCATION - APPLICABLE TO PART V (Sheet 2 of 2) EM170SB360606B.IDR IF THIS CONNECTOR IS BETWEEN THE SENSOR AND THE PIGTAIL, THE TEST POINT POSITION MUST BE IN THE SENSOR, AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. IF THIS CONNECTOR IS BETWEEN 2 SENSORS, THE TWO SENSORS MUST BE TESTED AT A DISTANCE FROM 102 TO 254 mm (4 TO 10 in) FROM THE CONNECTOR. THIS TEST POINT CORRESPONDS TO APPROXIMATELY 50% OF THE SENSORS LENGTH. TEST TWO SENSORS IN THIS POSITION.1 2 3 A ZONE 191 (PART V - LH SIDE) B A B ODS PN 04-90005-094A ODS LOOP JOINT ODS LOOP END 1 3 1 3 1 1 1 2 1 1 2 1 ODS PN 04-90005-096A ODS PN 04-90005-163A SERVICE BULLETIN SB190-36-0027 Page 58 of 118 Date: Apr 30, 2021 Revision No.: 02 - Sep 05, 2023 Copyright © by Embraer S.A. All rights reserved - See title page for details. User: jobragg0f - Printed By myTechCare - Dec 04/23 - 18:09:56 The text continues at https://openairdocs.org/service-documents/embraer/sb-190-36-0027/file/c74e0b80647c.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. Source documents are U.S. government works in the public domain, except the copies of manufacturers’ service documents, which belong to their rights holders.