1. DESCRIPTION This sheet transmits Revision 01 to Service Bulletin 190-53-0042. This is a complete reissue of the Bulletin. This revision incorporates the information presented in the Information Notice related to the previous issues of this Service Bulletin, as listed below: SB190-53-0042R00-IN01. 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: 13/Oct/2009. Revision 01: 28/Apr/2010. 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.A. SB EFFECTIVITY / 01 Changed Service Bulletin effectivity. 1.C. REASON / 02 Added reason of Revision 01. Figure 2 / 15 Changed text of Figure 02 (Sheet 02 of 02). 

# TRANSMITTAL LETTER

SB No.: 190-53-0042 PAGE: 1 of 1 Embraer Copyright © 2010. All rights reserved.FUSELAGE - INSPECTION OF THE REAR PRESSURE BULKHEAD RING 1. PLANNING INFORMATION A. SB EFFECTIVITY Aircraft affected: MODEL SN Embraer 190( ) and 195( ) 19000002, 19000004, 19000006 thru 19000108, 19000110 thru 19000139, 19000141 thru 19000157, 19000160, 19000165, 19000167 thru 19000176, 19000178 thru 19000199, 19000273 thru 19000276, 19000279 thru 19000286, 19000288 thru 19000295, 19000297 thru 19000304, and 19000309. In-production effectivity: The subject presented in this bulletin does not affect any in-production aircraft. B. CONCURRENT REQUIREMENTS None. C. REASON (1) HISTORY Drill marks were detected at the lower ring region of the rear pressure bulkhead, between the circumferential splice joint and rear skin (stringers 12 and 13). These marks might be caused by a drilling tool of the production line, during the aircraft assembly. 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 1 of 17 Embraer Copyright © 2010. All rights reserved.(2) OBJECTIVE To provide the instructions for doing a visual inspection for signs of drill marks at the LH/RH lower ring region of the rear pressure bulkhead and, if necessary, doing a repair in this area. (3) EXPECTED BENEFITS The purpose of this Service Bulletin is to rework possible tooling marks in the rear pressure bulkhead ring and thus to avoid that future cracks show in the future. (4) REVISION HISTORY REVISION 01: To include aircraft serial numbers 19000165, 19000167 thru 19000176, 19000178 thru 19000199, and 19000309 in the service bulletin effectivity, to exclude aircraft serial numbers 19000158, 19000277, and 19000287 and updated information of figure 2. This revision incorporates the Information Notices: SB190-53-0042R00-IN01. D. DESCRIPTION This Bulletin is divided into 2 PARTS, as follows: PART I VISUAL INSPECTION OF THE REAR PRESSURE BULKHEAD RING Applicable to: Refer to 1.A. SB EFFECTIVITY
. PART I of this bulletin consists of a visual inspection for signs of drill marks at the LH/RH lower ring region of the rear pressure bulkhead, between circumferential splice joint and rear skin (stringers 12 and 13). To gain access to the work area, it is necessary to open the rear fuselage door 314BR, located at zones 314 and 316. PART II REWORK OF THE REAR PRESSURE BULKHEAD RING Applicable to: Refer to 1.A. SB EFFECTIVITY
. The modification presented in PART II of this bulletin consists of the rework of the rear pressure bulkhead ring in order to eliminate the possible existence of drill marks. 

# SERVICE BULLETIN

SB No.: 190-53-0042 PAGE: 2 DATE: 13/Oct/2009 REVISION No.: 01 - 28/Apr/2010 Embraer Copyright © 2010. All rights reserved.To gain access to the work area, it is necessary to open the rear fuselage door 314BR, located at zones 314 and 316. NOTE: The modification presented in this bulletin affects the Fatigue Critical Structure (FCS); however, no change to the related Damage Tolerance Inspection (DTI) instructions is required. E. COMPLIANCE (1) APPLICABLE TO PART I Embraer recommends that PART I of this bulletin be accomplished by the time that the aircraft logs 20000 Flight Cycle(s). (2) APPLICABLE TO PART II If any drill mark(s) was (were) detected during the accomplishment of PART I of this bulletin, Embraer recommends that PART II of this bulletin be accomplished immediately after the accomplishment of PART I. 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: 0.2 man-hours. 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 3 Embraer Copyright © 2010. All rights reserved.– Inspection: 0.5 man-hours. – Modification: None. – Access closure: 0.2 man-hours. – Test: None. (2) APPLICABLE TO PART II – Access opening: 0.2 man-hours. – Inspection: None. – Modification: 1.5 man-hours. – Access closure: 0.2 man-hours. – Test: None. H. WEIGHT AND BALANCE None. I. SOFTWARE ACCOMPLISHMENT SUMMARY None. J. REFERENCES AMM 190/( ) Aircraft Maintenance Manual PART I - 52-45-00 - DOORS. AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD PRACTICES-AIRFRAME. CPM 190/( ) Corrosion Prevention Manual, Part I - 51-25-00 - STANDARD PRACTICES AND STRUCTURES. 

# SERVICE BULLETIN

SB No.: 190-53-0042 PAGE: 4 DATE: 13/Oct/2009 REVISION No.: 01 - 28/Apr/2010 Embraer Copyright © 2010. All rights reserved.ITEM 190/( ) Illustrated Tool and Equipment Manual. SRM 190/( ) Structural Repair Manual Part II - 51-10-03, 51-23-04, and 51-23-05 - STANDARD PRACTICES AND STRUCTURES. K. OTHER PUBLICATIONS AFFECTED None. 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 5 Embraer Copyright © 2010. All rights reserved.2. MATERIAL INFORMATION A. MATERIAL - PRICE AND AVAILABILITY (1) MATERIAL AVAILABLE FROM EMBRAER None. (2) MATERIAL AVAILABLE FROM OTHER VENDORS None. B. INDUSTRY SUPPORT INFORMATION None. 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. (1) TOP KITS AND KITS None. (2) MATERIAL TO BE PROCURED (a) Parts None. (b) Consumable Materials 

# SERVICE BULLETIN

SB No.: 190-53-0042 PAGE: 6 DATE: 13/Oct/2009 REVISION No.: 01 - 28/Apr/2010 Embraer Copyright © 2010. All rights reserved.The material below or equivalent, required for the accomplishment of this bulletin, should be procured from the operator’s inventories or from a local supplier. Applicable to PART II NEW PN DESCRIPTION OLD PN QTY DISP / Notes MS20470AD5-8D Rivet MS20470AD5-8D AR 6

- Sandpaper, aluminum-oxyde grain, No. 320 - AR - Alodine 1200 Alodine 1200 - AR 6/ [1] 10-P4-2/EC-117 Epoxy Primer - AR 6/ [2] DINITROL-AV-30 DINITROL-AV-30 - AR 6/ [3] 1. Chemical Compound for Conversion Coating on Aluminum (MIL-DTL-81706) ALODINE 1200 2. Epoxy Primer (MEP 10-059) 10-P4-2/EC-117 3. Type II Corrosion-Inhibiting Compound (MEP 10-063) DINITROL-AV-30 DISPOSITION: 6 = Apply as required QUANTITY: AR = As Required D. MATERIAL NECESSARY FOR EACH SPARE None. E. REIDENTIFIED PARTS None. F. TOOLING - PRICE AND AVAILABILITY The use of ITEM GSE 177 is suggested for the accomplishment of this bulletin. 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 7 Embraer Copyright © 2010. All rights reserved.3. ACCOMPLISHMENT INSTRUCTIONS NOTE: 1) For the purpose of this Service Bulletin, a General Visual Inspection (GVI) is: “A visual examination of an interior or exterior area, installation or assembly to detect obvious damage, failure or irregularity. This level of inspection is made from within touching distance, unless otherwise specified. A mirror may be necessary to enhance visual access to all exposed surfaces in the inspection area. This level of inspection is made under normally available lighting conditions such as daylight, hangar lighting, flashlight or drop-light and may require removal or opening of access panels or doors. Stands, ladders or platforms may be required to gain proximity to the area being checked.” 2) Obey all of the WARNINGS and CAUTIONS included in the referenced manuals and procedures. 3) 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. 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. WARNING : YOU MUST PREVENT ALL POSSIBLE OPERATION OF THE HORIZONTAL STABILIZER WHEN YOU WORK ON OR NEAR IT. THE HORIZONTAL STABILIZER MOVES QUICKLY AND WITH FORCE. IF THE STABILIZER MOVES WHEN PERSONS ARE IN THE TORSION BOX COMPARTMENT OR NEAR THE STABILIZER, IT CAN CAUSE INJURY TO THEM. WARNING : MAKE SURE THAT THERE WILL BE NO ACCIDENTAL OPERATION OF THE ELEVATOR AND RUDDER. AN ACCIDENTAL OPERATION OF THE ELEVATOR AND RUDDER CAN CAUSE INJURY TO PERSONS. B. Open the rear fuselage door 314BR. Refer to AMM SDS 52-45-00/1. 

# SERVICE BULLETIN

SB No.: 190-53-0042 PAGE: 8 DATE: 13/Oct/2009 REVISION No.: 01 - 28/Apr/2010 Embraer Copyright © 2010. All rights reserved.NOTE: To avoid damage to the aircraft, Embraer suggests the installation of the GSE177 in the rear fuselage. Refer to ITEM GSE 177. C. PART I – VISUAL INSPECTION OF THE REAR PRESSURE BULKHEAD RING (1) Do a visual inspection in the rear pressure bulkhead ring for drill marks, as indicated in Figure 1
. (a) If no drill mark(s) was (were) found, do Step 3.E. and on. (b) If any drill mark(s) was (were) found, do PART II (Step 3.D.) of this bulletin. D. PART II – REWORK OF THE REAR PRESSURE BULKHEAD RING WARNING : CLEANING PRODUCTS ARE TOXIC AND FLAMMABLE. A GOOD AIRFLOW MUST BE AVAILABLE WHEN YOU DO THE WORK IN CLOSED AREAS. (1) Locate and measure the damaged spot with respect to adjacent rivets and edges and then estimate the blend-out depth and width. Refer to Figure 2 and Figure 3, as applicable, for the allowable blend-out dimensions. NOTE: If no repair is defined in this document, contact Embraer Technical Support. (2) Check the blend-out outline for interference condition, in order to perform the blend-out as applicable (Figure 2 and/or Figure 3). The interference occurs when the distance from the blend-out boundary to the riveting line is 3 mm (0.118 in) or less. Refer to Figure 2 and Figure 3, as applicable. (3) For the blend-out that does not interfere with the existing fasteners, perform the blend-out as indicated in Figure 2. Refer to SRM PART II 51-10-03/1 - BLEND-OUT for the blend-out general instructions. 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 9 Embraer Copyright © 2010. All rights reserved.After that, touch-up the reworked area(s), using Chemical Compound for Conversion Coating on Aluminum (MIL-DTL-81706) ALODINE 1200 or similar, according to SRM PART II 51-23-04/1 - PRETREATMENT TO METAL PARTS, apply Epoxy Primer (MEP 10-059) 10-P4-2/EC-117 or similar, according to SRM PART II 51-23-05/1 - SURFACE PROTECTION - PRIMER, and then apply Type II Corrosion-Inhibiting Compound (MEP 10-063) DINITROL-AV-30 or similar, according to CPM PART 1 TASK 51-25-00-910-001-A. (4) For the blend-out that interferes with the existing fasteners, perform the blend-out as indicated in Figure 3. Refer to SRM PART II 51-10-03/1 - BLEND-OUT for the blend-out general instructions. After that, touch-up the reworked area(s), using Epoxy Primer (MEP 10-059) 10-P4-2/EC-117 or similar, according to SRM PART II 51-23-05/1 - SURFACE PROTECTION - PRIMER, and then, apply Type II Corrosion-Inhibiting Compound (MEP 10-063) DINITROL-AV-30 or similar, according to CPM PART 1 TASK 51-25-00-910-001-A. E. If applicable, remove GSE177 from the rear fuselage. Refer to ITEM GSE 177. F. Close the rear fuselage door 314BR. Refer to AMM SDS 52-45-00/1. G. Restore the aircraft to normal. H. Enter the accomplishment of PART I and/or PART II of this bulletin in the applicable documents. NOTE: 1) Please inform us by e-mail fleet.reliability@embraer.com.br of the aircraft manufacturer serial number and the SB incorporation date, specifying the SB Part(s) incorporated or whether the whole SB has been incorporated. This will enable Embraer to consider your aircraft configuration when providing future modifications. 2) To formally inform that the SB has been incorporated fleet-wide or that the SB will not be incorporated, so that Embraer can update the affected technical publications, use the “Service Bulletin Full-Fleet Incorporation Report” form, which is available on the Flyembraer portal (http://www.flyembraer.com). 

# SERVICE BULLETIN

SB No.: 190-53-0042 PAGE: 10 DATE: 13/Oct/2009 REVISION No.: 01 - 28/Apr/2010 Embraer Copyright © 2010. All rights reserved.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 to help us improve the quality of the SBs. 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 11 Embraer Copyright © 2010. All rights reserved.

### A ZONES

311 312



### A STGR 12 LH

STGR 13 LH

RING BULKHEAD (REF.) DOME (REF.) STGR 12 RH STGR 13 RH RING BULKHEAD (REF.)



### B CEM170SB530829A.DGN 

# SERVICE BULLETIN

SB No.: 190-53-0042 PAGE: 12 DATE: 13/Oct/2009 REVISION No.: 01 - 28/Apr/2010 FIGUR E 1 - VISUAL INSPECTION OF THE REAR PRESSURE BULKHEAD RING (SHEET 01 OF 02)

Embraer Copyright © 2010. All rights reserved.STGR 13RH STGR 12LH

STGR 13LH



### B C

D−D TYPICAL TH = 4.0 mm TH = 1.6 mm. D D D D 1 1

DOME

DOME

DOME

RING BULKHEAD

1 1 RING BULKHEAD RING BULKHEAD

STGR 12RH

FUSELAGE INSPECT THIS AREA INSPECT THIS AREA

INSPECT THIS AREA

INSPECT THIS AREA FOR THE PRESENCE OF DRILL MARKS.EM170SB530830A.DGN 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 13 FIGUR E 1 - VISUAL INSPECTION OF THE REAR PRESSURE BULKHEAD RING (SHEET 02 OF 02)

Embraer Copyright © 2010. All rights reserved.

### A ZONES

311 312



### A STGR 12 LH

STGR 13 LH

RING BULKHEAD (REF.) DOME (REF.) RING BULKHEAD (REF.)



### B B STGR 12 RH STGR 13 RHEM170SB530841A.DGN 

# SERVICE BULLETIN

SB No.: 190-53-0042 PAGE: 14 DATE: 13/Oct/2009 REVISION No.: 01 - 28/Apr/2010 FIGUR E 2 - BLEND-OUT WITH NO INTERFERENCE WITH EXISTING RIVETS (SHEET 01 OF 02)

Embraer Copyright © 2010. All rights reserved.BOUNDARY

1 2 3 4 5 3

6 2 4 5

6 TYPICAL

TYPICAL 1

L H

1

H = MAXIMUM BLEND−OUT DEPTH = 0.5 mm. 2 2

2 2 A B C

D BLEND−OUT BOUNDARY

LIMITS OF THE RIVETING AREA ARE 3 mm. RADIUS CENTERED IN THE RIVET HOLE A, B, C, D = DISTANCE FROM THE BLEND−OUT BOUNDARY TO THE RIVETING AREA MUST BE EQUAL TO OR GREATER THAN 0 mm.

BLEND−OUT LENGTH GREATER THAN 40 TIMES BLEND−OUT DEPTH. H L >40 

### B

HOLE OR RIVET DIAMETER = 5/32". BLEND−OUT RADIUS, WHICH MUST BE GREATER THAN 20 mm. 

### C CEM170SB530836B.DGN 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 15 FIGUR E 2 - BLEND-OUT WITH NO INTERFERENCE WITH EXISTING RIVETS (SHEET 02 OF 02)

Embraer Copyright © 2010. All rights reserved.

### A ZONES

311 312



### A STGR 12 LH

STGR 13 LH

RING BULKHEAD (REF.) DOME (REF.) RING BULKHEAD (REF.)



### B B STGR 12 RH STGR 13 RHEM170SB530842A.DGN 

# SERVICE BULLETIN

SB No.: 190-53-0042 PAGE: 16 DATE: 13/Oct/2009 REVISION No.: 01 - 28/Apr/2010 FIGUR E 3 - BLEND-OUT OVERLAPS - EXISTING FASTENERS HOLES (SHEET 01 OF 02)

Embraer Copyright © 2010. All rights reserved.3 4

1 2 3 4 FILLET RADIUS MINIMUM 12 mm. 

### C−C TYPICAL R 8.0 TYP.

1

2

REMOVE MATERIAL FROM A MAXIMUM OF 3 RIVETS IN A ROW RIVETS SHOULD BE REMOVED BEFORE THE BLEND−OUT. REINSTALL RIVETS AFTER COMPLETING THE REWORK BULKHEAD WEB BULKHEAD RING LEG 

### B C C

H

H = DEPTH OF THE REMOVED MATERIAL. D < 0.35 mm.EM170SB530837A.DGN 

# SERVICE BULLETIN

DATE: 13/Oct/2009 REVISION No.:01 - 28/Apr/2010 SB No.: 190-53-0042 PAGE: 17 FIGUR E 3 - BLEND-OUT OVERLAPS - EXISTING FASTENERS HOLES (SHEET 02 OF 02)

Embraer Copyright © 2010. All rights reserved.

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

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

Embraer Copyright © 2010. All rights reserved.