PNEUMATIC - PRECOOLER DEFLECTOR INSTALLATION AND SEALANT APPLICATION 1. PLANNING INFORMATION A. SB EFFECTIVITY Aircraft affected: MODEL SN Embraer 170( ) and 175( ) 17000002, 17000004 thru 17000013, and 17000015 thru 17000327. Affected component: None. In-production effectivity: Embraer 170( ) and 175( ) model aircraft SN 17000328 and on, have an equivalent modification factory-incorporated. B. CONCURRENT REQUIREMENTS (1) The accomplishment of PART I is required prior to the accomplishment of PART II. (2) The accomplishment of PART III is required prior to the accomplishment of PART IV. C. REASON (1) HISTORY Operators have reported the occurrence of ′′BLEED 1(2) LEAK′′ CAS messages displayed on the EICAS. Further analysis revealed the occurrence of hot air leakage in the pylon region, specifically, in the lower side of the Precooler Assembly. This leakage is affecting the pylon region and consequently, it can affect the pylon harnesses. 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 1 of 23 Copyright © 2011 by Embraer S.A. All rights reserved.(2) OBJECTIVE To install a Precooler deflector and to apply a specific sealant to the precooler assembly. (3) EXPECTED BENEFITS This modification is aimed at eliminating the possibility that hot air coming from the precooler assembly leaks inside the pylon, and to protect pylon harnesses, consequently reducing the instances of the ′′BLEED 1(2) LEAK′′ CAS messages coming into view. (4) REVISION HISTORY None. D. DESCRIPTION This Bulletin is divided into 4 PARTS, as follows: PART I PRECOOLER DEFLECTOR INSTALLATION - LH PYLON Applicable to: Applicable to 1.A. SB EFFECTIVITY

. The modification presented in PART I of this bulletin consists in installing a deflector together with the precooler, located in LH pylon, at zone 419. To do this, it is necessary to gain access to the work area, at the LH pylon by removing access panels 419QR, 419NR, 419RL, and 419ML. PART II SEALANT APPLICATION - LH PYLON Applicable to: Applicable to 1.A. SB EFFECTIVITY

. The modification presented in PART II of this bulletin consists in applying sealant to the two faces of the gasket located in LH pylon, at zone 419. To do this, it is necessary to gain access to the work area, at the LH pylon by removing access panels 419QR, 419NR, 419RL, 419ML, and remove LH Fan Air Valve. PART III PRECOOLER DEFLECTOR INSTALLATION - RH PYLON Applicable to: Applicable to 1.A. SB EFFECTIVITY

. 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 2 DATE: 23/Aug/2011 REVISION No.: Copyright © 2011 by Embraer S.A. All rights reserved.The modification presented in PART III of this bulletin consists in installing a deflector together with the precooler located in RH pylon, at zone 429. To do this, it is necessary to gain access to the work area, at the RH pylon by removing access panels 429SR, 429NR, 429PL, and 429ML. PART IV SEALANT APPLICATION - RH PYLON Applicable to: Applicable to 1.A. SB EFFECTIVITY

. The modification presented in PART IV of this bulletin consists in applying sealant to the two faces of the gasket located in RH pylon, at zone 429. To do this, it is necessary to gain access to the work area, at the RH pylon by removing access panels 429SR, 429NR, 429PL, 429ML, and remove RH Fan Air Valve. NOTE: The modification presented in this bulletin does not affect the Fatigue Critical Structure (FCS). 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 3 Copyright © 2011 by Embraer S.A. All rights reserved.E. COMPLIANCE (1) APPLICABLE TO PART I PART I of this bulletin may be accomplished at any time, at the operator’s discretion. (2) APPLICABLE TO PART II PART II of this bulletin may be accomplished at any time, at the operator’s discretion. (3) APPLICABLE TO PART III PART III of this bulletin may be accomplished at any time, at the operator’s discretion. (4) APPLICABLE TO PART IV PART IV of this bulletin may be accomplished at any time, at the operator’s discretion. F. APPROVAL The technical aspects of this Service Bulletin are approved by: Agência Nacional de Aviação Civil (ANAC). G. ESTIMATED MANPOWER This estimate is for direct labor only, performed by experienced personnel, and does not include the time to plan, prepare, or inspect the work. It is assumed that all the tools, parts, and other means are readily available when necessary. This estimate does not include the sealant, paint, or adhesive curing time. (1) APPLICABLE TO PART I – Access opening: 0.5 man-hours. – Inspection: None. 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 4 DATE: 23/Aug/2011 REVISION No.: Copyright © 2011 by Embraer S.A. All rights reserved.– Modification: 0.5 man-hours. – Access closure: 0.5 man-hours. – Test: None. NOTE: This estimate does not include the sealant, paint, or adhesive curing time. (2) APPLICABLE TO PART II – Access opening: 1.0 man-hour. – Inspection: None. – Modification: 1.0 man-hour. – Access closure: 1.0 man-hour. – Test: 0.5 man-hours. NOTE: This estimate does not include the sealant, paint, or adhesive curing time. (3) APPLICABLE TO PART III – Access opening: 0.5 man-hours. – Inspection: None. – Modification: 0.5 man-hours. – Access closure: 0.5 man-hours. – Test: None. NOTE: This estimate does not include the sealant, paint, or adhesive curing time. (4) APPLICABLE TO PART IV – Access opening: 1.0 man-hour. 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 5 Copyright © 2011 by Embraer S.A. All rights reserved.– Inspection: None. – Modification: 1.0 man-hour. – Access closure: 1.0 man-hour. – Test: 0.5 man-hours. NOTE: This estimate does not include the sealant, paint, or adhesive curing time. H. WEIGHT AND BALANCE (1) APPLICABLE TO PART I (a) Applicable to EMBRAER 170 – Change in basic weight: + 1.30 lb (+ 0.59 kg). – Change in basic moment: + 643.35 lb.in (+ 7.42 kg.m). (b) Applicable to EMBRAER 175 – Change in basic weight: + 1.30 lb (+ 0.59 kg). – Change in basic moment: + 685.83 lb.in (+ 7.91 kg.m). (2) APPLICABLE TO PART II – Change in basic weight: None. – Change in basic moment: None. (3) APPLICABLE TO PART III (a) Applicable to EMBRAER 170 – Change in basic weight: + 1.30 lb (+ 0.59 kg). – Change in basic moment: + 643.35 lb.in (+ 7.42 kg.m). 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 6 DATE: 23/Aug/2011 REVISION No.: Copyright © 2011 by Embraer S.A. All rights reserved.(b) Applicable to EMBRAER 175 – Change in basic weight: + 1.30 lb (+ 0.59 kg). – Change in basic moment: + 685.83 lb.in (+ 7.91 kg.m). (4) APPLICABLE TO PART IV – Change in basic weight: None. – Change in basic moment: None. I. SOFTWARE ACCOMPLISHMENT SUMMARY None. J. REFERENCES AMM 170/( ) Aircraft Maintenance Manual PART II - 06-43-00 - DIMENSIONS AND AREAS. AMM 170/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. AMM 170/( ) Aircraft Maintenance Manual PART II - 36-11-00, 36-11-08, and 36-11-09 - PNEUMATIC. K. OTHER PUBLICATIONS AFFECTED AIPC 170/( ) Aircraft Illustrated Parts Catalog - 36-11-08 - PNEUMATIC. 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 7 Copyright © 2011 by Embraer S.A. All rights reserved.2. MATERIAL INFORMATION A. MATERIAL - PRICE AND AVAILABILITY (1) MATERIAL AVAILABLE FROM EMBRAER The kit(s) below required for the accomplishment of PART I and PART III of this bulletin will be available from Embraer at no charge to the operator. Embraer will receive the ′′no charge′′ orders during a period of 24 months after the original release date of this service bulletin. The estimated delivery date will be provided by Embraer upon request. When ordering, specify SB 170-36-0019 and Top Kit PN presented in Table below, as applicable.

REF TOP KIT PN Unit Price (US$) TOP KIT EFFECTIVITY

01 BS1703600190001 366.15 Applicable to PART I and PART II/ Refer to 1.A. SB EFFECTIVITY 02 BS1703600190002 366.15 Applicable to PART III and PART IV/ Refer to 1.A. SB EFFECTIVITY (2) MATERIAL AVAILABLE FROM OTHER VENDORS None. B. INDUSTRY SUPPORT INFORMATION None. 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 8 DATE: 23/Aug/2011 REVISION No.: Copyright © 2011 by Embraer S.A. All rights reserved.C. MATERIAL NECESSARY FOR EACH AIRCRAFT When applicable, the use of alternative or similar parts in place of the one specified in the kits is allowable, provided that these alternative or similar parts are approved by Embraer as indicated in the related Embraer Technical Publications or through a formal Embraer communication channel. The necessary expendable or consumable parts presented in the AMM Tasks referred to in this bulletin should be procured from the operator’s inventories or ordered as spares. The complementary information, when necessary, is presented as Notes in the respective Table. For ordering information and Top Kit effectivity refer to section 2.A. MATERIAL - PRICE AND AVAILABILITY of this Bulletin. (1) TOP KITS AND KITS Kit Summary: Top Kit Composition (Kit PN / Quantity) Top Kit PN 171-14887-601 171-14887-602 BS1703600190001 01 - BS1703600190002 - 01 (a)
Kit PN 171-14887-601 NEW PN DESCRIPTION OLD PN QTY SUP QTY RQD DISP 171-15133-001 Deflector - 01 01 2/ [1] AN4C7A Bolt AN4-7A or AN4C6A 02 02 2/ [1] 1. Applicable to PART I 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 9 Copyright © 2011 by Embraer S.A. All rights reserved.Kit PN 171-14887-601 NEW PN DESCRIPTION OLD PN QTY SUP QTY RQD DISP NAS1149C432R Washer NAS1149C432R 02 02 2 / [1] 170-16603-001 Interface Gasket 170-16603-001 01 01 3/ [2] 2873-450 Seal 2873-450 02 02 3/ [2] 1. Applicable to PART I 2. Applicable to PART II (b)
Kit PN 171-14887-602 NEW PN DESCRIPTION OLD PN QTY SUP QTY RQD DISP 171-15133-001 Deflector - 01 01 2/ [1] AN4C7A Bolt AN4-7A or AN4C6A 02 02 2/ [1] NAS1149C432R Washer NAS1149C432R 02 02 2/ [1] 170-16603-001 Interface Gasket 170-16603-001 01 01 3/ [2] 2873-450 Seal 2873-450 02 02 3/ [2] 1. Applicable to PART III. 2. Applicable to PART IV. (2) MATERIAL TO BE PROCURED (a) Parts None. (b) Consumable Materials 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 10 DATE: 23/Aug/2011 REVISION No.: Copyright © 2011 by Embraer S.A. All rights reserved.The material below or equivalent, required for the accomplishment of PART II and PART IV of this bulletin, should be procured from the operator’s inventories or from a local supplier. Applicable to PART II and PART IV NEW PN DESCRIPTION OLD PN QTY DISP/ Notes LOCTITE 5920 Sealant - AR 6/ [1] [2] TT-I-735 Isopropyl Alcohol - AR 6/ [1] [2] 1. High Temp Silicone Sealant (-) LOCTITE 5920. 2. Applicable to PART II and PART IV. DISPOSITION: 2 = Incorporate part bearing NEW PN 3 = Replace part bearing OLD PN with part bearing NEW PN 6 = Apply as required QUANTITY: AR = As Required D. MATERIAL NECESSARY FOR EACH SPARE None. E. REIDENTIFIED PARTS None. F. TOOLING - PRICE AND AVAILABILITY Whenever required, the necessary tooling presented in the AMM Tasks referred to in this bulletin, should be procured from the operator’s inventories or ordered as spares. 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 11 Copyright © 2011 by Embraer S.A. All rights reserved.3. ACCOMPLISHMENT INSTRUCTIONS NOTE: 1) Obey all of the WARNINGS and CAUTIONS included in the referenced manuals and procedures. 2) The Manuals and other documents are referred to by acronyms or using a simplified form. Refer to section 1.J. REFERENCES for a more complete definition. 3) This Service Bulletin effectivity is divided into 04 PARTS. The SB PARTS are featured to allow their independent accomplishment. The steps below outline the general accomplishment instructions. The detailed sequence is included in the respective figure, when necessary. A. 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. PART I – PRECOOLER DEFLECTOR INSTALLATION - LH PYLON (1) Remove and retain access panels 419QR, 419NR, 419RL, and 419ML. Refer to AMM TASK 06-43-00-800-801-A/100 - Powerplant and Pylon Access Doors and Panels to get the applicable Aircraft Maintenance Manual (AMM) removal task. (2) Install deflector PN 171-15133-001 to the LH pylon. Refer to Figure 1

. (3) Reinstall access panels 419QR, 419NR, 419RL, and 419ML. Refer to AMM TASK 06-43-00-800-801-A/100 - Powerplant and Pylon Access Doors and Panels to get the applicable Aircraft Maintenance Manual (AMM) installation task. (4) Enter the accomplishment of PART I of this bulletin in the applicable documents. (5) Restore the aircraft to normal. C. PART II – SEALANT APPLICATION - LH PYLON (1) Remove and retain LH Fan Air Valve. Refer to AMM TASK 36-11-09-000-801-A/400 - Fan Air Valve - Removal. 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 12 DATE: 23/Aug/2011 REVISION No.: Copyright © 2011 by Embraer S.A. All rights reserved.(2) Apply Sealant to the LH precooler region as indicated in Figure 2

. (3) Reinstall LH Fan Air Valve. Refer to AMM TASK 36-11-09-400-801-A/400 - Fan Air Valve - Installation. (4) Carry Out the operational test of the engine bleed system, according to AMM TASK 36-11-00-710-802-A/500 - Engine Pneumatic-Bleed-System in Idle Condition - Operational Test. (5) Enter the accomplishment of PART II of this bulletin in the applicable documents. (6) Restore the aircraft to normal. D. PART III – PRECOOLER DEFLECTOR INSTALLATION - RH PYLON (1) Remove and retain access panels 429SR, 429NR, 429PL, and 429ML. Refer to AMM TASK 06-43-00-800-801-A/100 - Powerplant and Pylon Access Doors and Panels to get the applicable Aircraft Maintenance Manual (AMM) removal task. (2) Install deflector PN 171-15133-001 to the RH pylon. Refer to Figure 1

. (3) Reinstall access panels 429SR, 429NR, 429PL, and 429ML. Refer to AMM TASK 06-43-00-800-801-A/100 - Powerplant and Pylon Access Doors and Panels to get the applicable Aircraft Maintenance Manual (AMM) installation task. (4) Enter the accomplishment of PART III of this bulletin in the applicable documents. (5) Restore the aircraft to normal. E. PART IV – SEALANT APPLICATION - RH PYLON (1) Remove and retain RH Fan Air Valve, according to AMM TASK 36-11-09-000-801- A/400 - Fan Air Valve - Removal. (2) Apply Sealant to the RH precooler region as indicated Figure 2

. (3) Reinstall and retain RH Fan Air Valve. Refer to AMM TASK 36-11-09-400-801-A/400 - Fan Air Valve - Installation. 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 13 Copyright © 2011 by Embraer S.A. All rights reserved.(4) Carry Out the operational test of the engine bleed system, according to AMM TASK 36-11-00-710-802-A/500 - Engine Pneumatic-Bleed-System in Idle Condition - Operational Test. (5) Enter the accomplishment of PART IV of this bulletin in the applicable documents. (6) Restore the aircraft to normal. NOTE: 1) Please inform us by e-mail fleet.reliability@embraer.com.br of the aircraft manufacturer serial number and the SB incorporation date, specifying the SB Part(s) incorporated or whether the whole SB has been incorporated. This will enable Embraer to consider your aircraft configuration when providing future modifications. 2) To formally inform that the SB has been incorporated fleet-wide or that the SB will not be incorporated, so that Embraer can update the affected technical publications, use the “Service Bulletin Full-Fleet Incorporation Report” form, which is available on the Flyembraer portal (http://www.flyembraer.com). 3) Use the attached “Service Bulletin Evaluation” form to send us your comments regarding this SB. Your feedback will be much appreciated as an aid for us to improve the quality of the SBs. 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 14 DATE: 23/Aug/2011 REVISION No.: Copyright © 2011 by Embraer S.A. All rights reserved.1. Remove and discard existing bolt and washer (02 positions). Refer Detail B (PRE-MOD). 2. Position and install deflector PN 171-15133-001 (01 position), using washer PN NAS1149C0432R (02 positions) and Screw PN AN4C7A (02 positions). Refer to Detail C, Detail B (POST-MOD) and Detail D. NOTE: Apply torque 9.6 - 11.9 N.m (85 - 105 lb.in). 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 15 FIGURE 1 - DEFLECTOR INSTALLATION (SHEET 01 OF 05)

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

### A B 

### A

B PRECOOLER


### C

BOLT (02 POSITIONS) WASHER (02 POSITIONS) (REMOVE AND DISCARD)EM170SB360335A.DGN 

### A

ZONE 419 ZONE

429

LEFT SIDE SHOWN RIGHT SIDE OPPOSITE

1

PRE − MOD 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 16 DATE: 23/Aug/2011 REVISION No.: FIGUR E 1 - DEFLECTOR INSTALLATION (SHEET 02 OF 05)

Copyright © 2011 by Embraer S.A. All rights reserved.1 1EM170SB360336A.DGN 

### C

AUXILIAR VIEW 

### C 1 C 1 PRECOOLER (REF.)

DEFLECTOR PN 171−15133−001 (01 POSITION) WASHER PN NAS1149C0432R (02 POSITIONS) SCREW PN AN4C7A (02 POSITIONS) (POSITION) (INSTALL)

1 TORQUE: 9.6 − 11.9 N.m (85 − 105 lb.in) 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 17 FIGURE 1 - DEFLECTOR INSTALLATION (SHEET 03 OF 05)

Copyright © 2011 by Embraer S.A. All rights reserved.AUXILIAR VIEW 1EM170SB360337A.DGN 

### D

DEFLECTOR PN 171−15133−001 (01 POSITION) WASHER PN NAS1149C0432R (02 POSITIONS) SCREW PN AN4C7A (02 POSITIONS) (POSITION) (INSTALL)

POST − MOD 

### B B 1



### B 1 2

1 TORQUE: 9.6 − 11.9 N.m (85 − 105 lb.in) 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 18 DATE: 23/Aug/2011 REVISION No.: FIGUR E 1 - DEFLECTOR INSTALLATION (SHEET 04 OF 05)

Copyright © 2011 by Embraer S.A. All rights reserved.2 1

AUXILIAR VIEW 

### D D 1



### D 1EM170SB360338A.DGN DEFLECTOR PN 171−15133−001 (01 POSITION) WASHER PN NAS1149C0432R (02 POSITIONS) SCREW PN AN4C7A (02 POSITIONS) (POSITION) (INSTALL)

1 TORQUE: 9.6 − 11.9 N.m (85 − 105 lb.in) 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 19 FIGURE 1 - DEFLECTOR INSTALLATION (SHEET 05 OF 05)

Copyright © 2011 by Embraer S.A. All rights reserved.1. Using task AMM MPP 36-11-08/401 - PRECOOLER - REMOVAL/INSTALLATION as reference, remove and retain the existing outlet duct, remove and discard interface gasket PN 170-16603-001, and remove and retain deflector 171-15133-001 from the low part of the precooler. NOTE: It is not necessary to remove the precooler. 2. With a clean cloth wet with Isopropyl Alcohol (TT-I-735) TT-I-735 , clean the faying surface of the precooler and outlet duct assy. If any sign of sealant is detected, remove the sealant using a polyethylene spatula to help in the sealant removal. 3. On a bench, apply High Temp Silicone Sealant (-) LOCTITE 5920 to one side of the new interface gasket PN 170-16603-001, and then position the wet side of the interface gasket PN 170-16603-001 on the precooler. 4. On a bench, apply High Temp Silicone Sealant (-) LOCTITE 5920 to the faying surface of the Outlet duct and then position it in the interface gasket PN 170-16603-001 already positioned in the installation position. 5. Use a polyethylene spatula to remove the excess of the sealant from the outside of the precooler. 6. Through the Outlet duct, use a polyethylene spatula to smooth the sealant from the internal and external sides of the precooler. 7. Using task AMM MPP 36-11-08/401 - PRECOOLER - REMOVAL/INSTALLATION as reference, reinstall the existing outlet duct assy, install new interface gasket PN 170-16603-001, and reinstall deflector 171-15133-001 using the retained bolts and washers. NOTE: Use a torque wrench to torque the bolts to 9.6 - 11.9 N.m (85 - 105 lb.in). 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 20 DATE: 23/Aug/2011 REVISION No.: FIGUR E 2 - SEALANT APPLICATION (SHEET 01 OF 04)

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

### B 

### A

B DEFLECTOR PN 171−15133−001 (REMOVE AND RETAIN) (REINSTALL) BOLT (06 POSITIONS) WASHER (06 POSITIONS) (REMOVE AND RETAIN) (REINSTALL) INTERFACE GASKET PN 170−16603−001 (REMOVE AND DISCARD) PN 170−16603−001 (APPLY SEALANT) (POSITION) (INSTALL) 

### C

DEM170SB360339A.DGN PRECOOLER (CLEAN) 1 2

1 2 137

7 7 4 7 OUTLET DUCT (REMOVE AND RETAIN) (CLEAN) (APPLY SEALANT) (REINSTALL) LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 

### A A

ZONE 419 ZONE

429

FAN AIR VALVE (REF.) 

### E 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 21 FIGURE 2 - SEALANT APPLICATION (SHEET 02 OF 04)

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



### CEM170SB360340A.DGN


### D 247 7 INTERFACE GASKET PN 170−16603−001 (ON THE BENCH, CLEAN AND APPLY SEALANT) (POSITION THE WET SIDE TO THE PRECOOLER) (INSTALL)

OUTLET DUCT (ON THE BENCH, CLEAN AND APPLY SEALANT) (POSITION TO THE INTERFACE GASKET) (INSTALL) 

# SERVICE BULLETIN

SB No.: 170-36-0019 PAGE: 22 DATE: 23/Aug/2011 REVISION No.: FIGUR E 2 - SEALANT APPLICATION (SHEET 03 OF 04)

Copyright © 2011 by Embraer S.A. All rights reserved.THROUGH THE OUTLET DUCT (SMOOTH THE SEALANT)

6



### EEM170SB360341A.DGN 

# SERVICE BULLETIN

DATE: 23/Aug/2011 REVISION No.: SB No.: 170-36-0019 PAGE: 23 FIGURE 2 - SEALANT APPLICATION (SHEET 04 OF 04)

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

### SERVICE BULLETIN EVALUATION
THE PURPOSE OF THIS FORM IS TO COLLECT DATA THAT WILL BE USED TO IMPROVE THE QUALITY OF OUR SERVICE BULLETINS AND UPDATE THE TECHNICAL PUBLICATIONS. PLEASE FILL IN FORM AND RETURN IT TO: EMBRAER - EMPRESA BRASILEIRA DE AERONÁUTICA S.A. EFTC - SERVICE BULLETIN ENGINEERING AV. BRIGADEIRO FARIA LIMA, 2170 SÃO JOSÉ DOS CAMPOS - SP - 12227-901 BRASIL Fax: + 55 12 3927-6600 (ext. 1624) e-mail: fleet.reliability@embraer.com.br S.B. Title: S.B.: (Number / Rev.) Operator: SB Implementation Report Aircraft Serial Number or Registration Number: Incorporation Date: Aircraft Flight Hours: Aircraft Landings:
POST-ACCOMPLISHMENT EVALUATION: (Check applicable squares below) ESTIMATED MANPOWER: [ ] OK [ ] NOT OK (Explain Below) MATERIAL & KITS: [ ] OK [ ] NOT OK (Explain Below) ACCOMPLISHMENT INSTRUCTIONS: [ ] OK [ ] NOT OK (Explain Below) FIGURES: [ ] OK [ ] NOT OK (Explain Below) SB GENERAL EVALUATION: [ ] OK [ ] NOT OK (Explain Below) COMMENTS: (Bulletin quality/ Difficulties found at the time of incorporation/ Suggested improvements/ Other)

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

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