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.

1) Please inform us by e-mail fleet.reliability@embraer.com.br of the aircraft NOTE:

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.:

FIGURE 1 - DEFLECTOR INSTALLATION

(SHEET 02 OF 05)

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

EM170SB360336A.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

1

EM170SB360337A.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.:

FIGURE 1 - DEFLECTOR INSTALLATION

(SHEET 04 OF 05)

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

AUXILIAR VIEW

D

D 1

D 1

EM170SB360338A.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.:

FIGURE 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

D

EM170SB360339A.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

C

EM170SB360340A.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.:

FIGURE 2 - SEALANT APPLICATION

(SHEET 03 OF 04)

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

OUTLET DUCT

(SMOOTH THE SEALANT)

6

E

EM170SB360341A.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.