1. DESCRIPTION

This sheet transmits Revision 01 to Service Bulletin 190-52-0038.

This is a complete reissue of the Bulletin.

2. ADDITIONAL ACTION

Aircraft that have complied with the previous issue of this bulletin need an additional action,

according to PART II. After the accomplishment of PART II, if applicable, the accomplishment

of PART III may be necessary.

3. RECORD OF REVISION

Basic issue: 10/Feb/2011.

Revision 01: 01/Aug/2011.

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

TITLE / 01 Updated information.

1. PLANNING INFORMATION

1.A. SB EFFECTIVITY 01 and 02 Changed SB effectivity and divided SB in 3

GROUPS.

1.C. REASON / 03 Added reason of Revision 01.

1.D. DESCRIPTION / 03 and 04 Updated information and divided bulletin in 3

PARTS.

1.E. COMPLIANCE / 04 Updated information and divided bulletin in 3

PARTS.

1.G. ESTIMATED MANPOWER / 05 and 06 Updated information and divided bulletin in 3

PARTS.

1.H. WEIGHT AND BALANCE / 06 Updated information and divided bulletin in 3

PARTS.

2. MATERIAL INFORMATION

2.A. MATERIAL - PRICE AND AVAILABILITY / 08 Included additional kit.

2.C. MATERIAL NECESSARY FOR EACH AIRCRAFT / 09 thru 11 Included additional kit.

2.E. REIDENTIFIED PARTS / 12, 14 thru 16 Updated part number information.

TRANSMITTAL LETTER

SB No.: 190-52-0038

PAGE: 1 of 2

Copyright © 2011 by Embraer S.A. All rights reserved.
TOPIC/PAGE DESCRIPTION OF REVISION

3. ACCOMPLISHMENT INSTRUCTIONS / 17 and

18

Updated modification procedures and divided in 3

PARTs.

Figure 1 / 20, 23 thru 26 Included additional procedure and update illustration.

Figure 2 / 27 thru 29 Included additional procedure.

Figure 3 / 30 thru 33 Included additional procedure.

TRANSMITTAL LETTER

SB No.: 190-52-0038

PAGE: 2

Copyright © 2011 by Embraer S.A. All rights reserved.
DOORS - COCKPIT DOOR PASSIVE LOCK AND HINGES REPLACEMENT

This bulletin supersedes SB190-52-0035

1. PLANNING INFORMATION

A. SB EFFECTIVITY

Aircraft affected:

(1) GROUP 1

MODEL SN

Embraer 190( ) and 195( ) 19000001 thru 19000108, 19000110 thru 19000139,

19000141 thru 19000158, 19000160 thru 19000176,

19000178 thru 19000202, 19000204 thru 19000224,

19000226 thru 19000235, 19000237 thru 19000242,

19000244 thru 19000260, 19000262 thru 19000277,

19000279 thru 19000295, 19000297 thru 19000306,

19000308 thru 19000316, 19000318 thru 19000361,

and 19000363 thru 19000412, which have not been

modified according to the previous issue of this

bulletin.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 1 of 33

Copyright © 2011 by Embraer S.A. All rights reserved.
(2) GROUP 2

MODEL SN

Embraer 190( ) and 195( ) 19000001 thru 19000108, 19000110 thru 19000139,

19000141 thru 19000158, 19000160 thru 19000176,

19000178 thru 19000202, 19000204 thru 19000224,

19000226 thru 19000235, 19000237 thru 19000242,

19000244 thru 19000260, 19000262 thru 19000277,

19000279 thru 19000295, 19000297 thru 19000306,

19000308 thru 19000316, 19000318 thru 19000361,

and 19000363 thru 19000412, which have already

been modified according to the previous issue of this

bulletin.

(3) GROUP 3

MODEL SN

Embraer 190( ) and 195( ) 19000413 thru 19000437, 19000439 thru 19000444,

19000446, 19000447, 19000450, and 19000453.

Affected component:

None.

In-production effectivity:

Embraer 190( ) and 195( ) model aircraft SN 19000445, 19000448, 19000449, 19000451,

19000452, 19000454 and on have an equivalent modification factory-incorporated.

B. CONCURRENT REQUIREMENTS

The accomplishment of SB190-52-0037 original issue or a subsequent approved revision

is required in conjunction with the accomplishment of this Service Bulletin.

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 2

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

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

(1) HISTORY

The screws that attach the passive lock striker may become loose due to the aircraft

natural vibration. This can result in the loss of the passive lock striker and the door

falling off of its hinges in the cockpit, as a consequence.

(2) OBJECTIVE

To replace the existing passive lock striker, quick-release pin and also to inspect and

replace the upper and lower hinges of the cockpit door, if necessary.

(3) EXPECTED BENEFITS

To improve the passive lock striker attachment in order to avoid the striker from

coming loose over the time.

(4) REVISION HISTORY

REVISION 01: This revision has been issued to improve the Service Bulletin

solution and included PART II and PART III as additional action.

D. DESCRIPTION

This Bulletin is divided into 3 PARTS, as follows:

PART I REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

Applicable to: GROUP 1.

PART I of this bulletin provides instructions to replace the existing passive lock striker and

quick-release pin of the cockpit door.

To do this, it is necessary to gain access to the cockpit area.

PART II INSPECTION OF COCKPIT DOOR HINGES

Applicable to: GROUP 1, GROUP 2 AND GROUP 3.

PART II of this bulletin provides instructions to inspect the upper and lower hinges located

in the cockpit door.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 3

Copyright © 2011 by Embraer S.A. All rights reserved.
To do this, it is necessary to gain access to the cockpit area.

PART III REPLACEMENT OF COCKPIT DOOR HINGES

Applicable to: GROUP 1, GROUP 2 AND GROUP 3.

PART III of this bulletin provides instructions to replace the existing upper and lower

hinges located in the cockpit door and cockpit door jambs.

To do this, it is necessary to gain access to the cockpit area.

NOTE: The modification presented in this bulletin does not affect the Fatigue

Critical Structure (FCS).

E. COMPLIANCE

(1) APPLICABLE TO PART I

Embraer recommends that PART I of this bulletin be accomplished within the next

3000 Flight Hour(s) after the issuance of revision 01 of this bulletin revision.

(2) APPLICABLE TO PART II

Embraer recommends that PART II of this bulletin be accomplished within the next

3000 Flight Hour(s) after the issuance of revision 01 of this bulletin revision.

(3) APPLICABLE TO PART III

Embraer recommends that PART III of this bulletin be accomplished after the

accomplishment of PART II, and within the next 3000 Flight Hour(s) after the

issuance of revision 01 of this bulletin revision.

F. APPROVAL

The technical aspects of this Service Bulletin are approved by: Agência Nacional de

Aviação Civil (ANAC).

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 4

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

Copyright © 2011 by Embraer S.A. All rights reserved.
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: 1.0 man-hours.

– Inspection: None.

– Modification: 1.0 man-hours.

– Access closure: 1.0 man-hours.

– Test: None.

(2) APPLICABLE TO PART II

– Access opening: 1.0 man-hours.

– Inspection: 0.4 man-hours.

– Modification: None.

– Access closure: 1.0 man-hours.

– Test: None.

(3) APPLICABLE TO PART III

– Access opening: 1.0 man-hours.

– Inspection: None.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 5

Copyright © 2011 by Embraer S.A. All rights reserved.
– Modification: 0.4 man-hours.

– Access closure: 1.0 man-hours.

– Test: None.

H. WEIGHT AND BALANCE

(1) APPLICABLE TO PART I

– Change in basic weight: + 0.179 lb (+ 0.081 kg).

– Change in basic moment: + 25.933 lb.in (+ 0.298 kg.m).

(2) APPLICABLE TO PART II

None.

(3) APPLICABLE TO PART III

– Change in basic weight: + 0.170 lb (+ 0.077 kg).

– Change in basic moment: + 24.623 lb.in (+ 0.283 kg.m).

I. SOFTWARE ACCOMPLISHMENT SUMMARY

None.

J. REFERENCES

AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 and 20-10-09 -

STANDARD PRACTICES-AIRFRAME.

AMM 190/( ) Aircraft Maintenance Manual PART II - 52-51-01 - DOORS.

SB190-52-0035 DOORS - COCKPIT DOOR PASSIVE LOCK MODIFICATION.

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 6

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

Copyright © 2011 by Embraer S.A. All rights reserved.
SB190-52-0037 DOORS - COCKPIT DOOR INSPECTION &sol;

ADJUSTMENT.

K. OTHER PUBLICATIONS AFFECTED

AIPC 190/( ) Aircraft Illustrated Parts Catalog - 52-51-01 - DOORS.

AMM 190/( ) Aircraft Maintenance Manual PART II - 52-51-01 - DOORS.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

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 below, required for the accomplishment of this bulletin, will be available from

Embraer at no charge to the operator during a period of 36 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 190-52-0038 and Top Kit PN presented in Table below,

as applicable.

REF TOP KIT PN

Unit

Price

(US$)

TOP KIT EFFECTIVITY

01 BS1905200380001 834.08 Applicable to PART I

02 BS1905200380102 4,011.13 Applicable to PART III

(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.

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 8

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

Copyright © 2011 by Embraer S.A. All rights reserved.
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 171-14451-601 171-14877-601

BS1905200380001 01 -

BS1905200380102 - 01

(a)

Kit PN 171-14451-601

NEW PN DESCRIPTION OLD PN QTY

SUP

QTY

RQD

DISP/

NOTES

171−08458−001 Placard

171−08458−001 or IAP00005-01

01 01 3

171-14450-401 Striker 170-96130-001 01 01 3

MS16624-2025 Ring MS16624-2025 01 01 7

NAS1149D0432K Washer - 01 01 2

MS35338-137 Washer - 02 02 2

NAS1149DN816K Washer NAS1149DN816K 02 02 3

- Screw

MS24693-C5 or

MS24693-C6

- 02 5

- Pin 170-96097-001 - 01 8

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 9

Copyright © 2011 by Embraer S.A. All rights reserved.
Kit PN 171-14451-601

NEW PN DESCRIPTION OLD PN QTY

SUP

QTY

RQD

DISP/

NOTES

- Lanyard cable BLC4BA11SL4A7 - 01 5

- Shim 170-96140-001 - 01 5

(b)

Kit PN 171-14877-601

NEW PN DESCRIPTION OLD PN QTY

SUP

QTY

RQD

DISP/

NOTES

170-96133-405 Lower Hinge 170-96133-401 01 01 3 / [1]

170-96137-403 Upper hinge 170-96137-401 01 01 3 / [1]

170-96068-403 Upper hinge 170-96068-401 01 01 3 / [2]

170-96076-403 Lower Hinge 170-96076-401 01 01 3 / [2]

171-12687-001 Shim - 01 01 2 / [2]

171-12686-001 Shim - 01 01 2 / [2]

PE25041-055-03 Spring pin PE25041-055-03 02 02 7 / [2]

1. Applicable to cockpit door jambs.

2. Applicable to cockpit door.

DISPOSITION: 2 = Incorporate part bearing NEW PN

3 = Replace part bearing OLD PN with part bearing NEW

PN

5 = Discard part bearing OLD PN

7 = Replace with part bearing same PN

8 = Reuse part bearing OLD PN

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 10

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

Copyright © 2011 by Embraer S.A. All rights reserved.
(2) MATERIAL TO BE PROCURED

(a) Parts

None.

(b) Consumable Materials

None.

D. MATERIAL NECESSARY FOR EACH SPARE

None.

E. REIDENTIFIED PARTS

The information necessary to reidentify the parts is presented in table below:

DESCRIPTION OLD PN NEW PN

Cockpit Door Assy 170-96021-401 170-96021-637

Cockpit Door Assy 170-96021-601 170-96021-625

Cockpit Door Assy 170-96021-605 170-96021-629

Cockpit Door Assy 170-96021-609 170-96021-633

Cockpit Door Assy 170-96021-611 170-96021-637

Cockpit Door Assy 170-96021-615 170-96021-625

Cockpit Door Assy 170-96021-619 170-96021-629

Cockpit Door Assy 170-96021-623 170-96021-633

Cockpit Door Assy 170-96021-403 170-96021-639

Cockpit Door Assy 170-96021-603 170-96021-627

Cockpit Door Assy 170-96021-607 170-96021-631

Cockpit Door Assy 170-96021-407 170-96021-635

Cockpit Door Assy 170-96021-613 170-96021-639

Cockpit Door Assy 170-96021-617 170-96021-627

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 11

Copyright © 2011 by Embraer S.A. All rights reserved.
DESCRIPTION OLD PN NEW PN

Cockpit Door Assy 170-96021-621 170-96021-631

Cockpit Door Assy 170-96021-409 170-96021-635

Cockpit Door Assy 170-96170-401 170-96170-621

Cockpit Door Assy 170-96170-601 170-96170-615

Cockpit Door Assy 170-96170-603 170-96170-617

Cockpit Door Assy 170-96170-605 170-96170-619

Cockpit Door Assy 170-96170-607 170-96170-621

Cockpit Door Assy 170-96170-609 170-96170-615

Cockpit Door Assy 170-96170-611 170-96170-617

Cockpit Door Assy 170-96170-613 170-96170-619

Cockpit Door Assy 170-96198-401 170-96198-625

Cockpit Door Assy 170-96198-601 170-96198-613

Cockpit Door Assy 170-96198-603 170-96198-617

Cockpit Door Assy 170-96198-405 170-96198-621

Cockpit Door Assy 170-96198-605 170-96198-625

Cockpit Door Assy 170-96198-609 170-96198-613

Cockpit Door Assy 170-96198-611 170-96198-617

Cockpit Door Assy 170-96198-403 170-96198-615

Cockpit Door Assy 170-96198-607 170-96198-615

Cockpit Door Assy 170-96198-407 170-96198-623

Cockpit Door Assy 170-98752-401 170-98752-621

Cockpit Door Assy 170-98752-601 170-98752-615

Cockpit Door Assy 170-98752-603 170-98752-617

Cockpit Door Assy 170-98752-605 170-98752-619

Cockpit Door Assy 170-98752-607 170-98752-621

Cockpit Door Assy 170-98752-609 170-98752-615

Cockpit Door Assy 170-98752-611 170-98752-617

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 12

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

Copyright © 2011 by Embraer S.A. All rights reserved.
DESCRIPTION OLD PN NEW PN

Cockpit Door Assy 170-98752-613 170-98752-619

Cockpit Door Assy 171-03990-401 171-03990-637

Cockpit Door Assy 171-03990-601 171-03990-625

Cockpit Door Assy 171-03990-605 171-03990-629

Cockpit Door Assy 171-03990-609 171-03990-633

Cockpit Door Assy 171-03990-611 171-03990-637

Cockpit Door Assy 171-03990-615 171-03990-625

Cockpit Door Assy 171-03990-619 171-03990-629

Cockpit Door Assy 171-03990-623 171-03990-633

Cockpit Door Assy 171-03990-403 171-03990-639

Cockpit Door Assy 171-03990-603 171-03990-627

Cockpit Door Assy 171-03990-607 171-03990-631

Cockpit Door Assy 171-03990-407 171-03990-635

Cockpit Door Assy 171-03990-613 171-03990-639

Cockpit Door Assy 171-03990-617 171-03990-627

Cockpit Door Assy 171-03990-621 171-03990-631

Cockpit Door Assy 171-03990-409 171-03990-635

Cockpit Door Assy 171-04002-401 171-04002-625

Cockpit Door Assy 171-04002-601 171-04002-613

Cockpit Door Assy 171-04002-603 171-04002-617

Cockpit Door Assy 171-04002-405 171-04002-621

Cockpit Door Assy 171-04002-605 171-04002-625

Cockpit Door Assy 171-04002-609 171-04002-613

Cockpit Door Assy 171-04002-611 171-04002-617

Cockpit Door Assy 171-04002-403 171-04002-615

Cockpit Door Assy 171-04002-607 171-04002-615

Cockpit Door Assy 171-04002-407 171-04002-623

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 13

Copyright © 2011 by Embraer S.A. All rights reserved.
DESCRIPTION OLD PN NEW PN

Cockpit Door Assy 171-04008-401 171-04008-625

Cockpit Door Assy 171-04008-601 171-04008-613

Cockpit Door Assy 171-04008-603 171-04008-617

Cockpit Door Assy 171-04008-405 171-04008-621

Cockpit Door Assy 171-04008-605 171-04008-625

Cockpit Door Assy 171-04008-609 171-04008-613

Cockpit Door Assy 171-04008-611 171-04008-617

Cockpit Door Assy 171-04008-403 171-04008-615

Cockpit Door Assy 171-04008-607 171-04008-615

Cockpit Door Assy 171-04008-407 171-04008-623

Cockpit Door Assy 171-04727-401 171-04727-625

Cockpit Door Assy 171-04727-601 171-04727-613

Cockpit Door Assy 171-04727-603 171-04727-617

Cockpit Door Assy 171-04727-405 171-04727-621

Cockpit Door Assy 171-04727-605 171-04727-625

Cockpit Door Assy 171-04727-609 171-04727-613

Cockpit Door Assy 171-04727-611 171-04727-617

Cockpit Door Assy 171-04727-403 171-04727-615

Cockpit Door Assy 171-04727-607 171-04727-615

Cockpit Door Assy 171-04727-407 171-04727-623

Cockpit Door Assy 171-08455-401 171-08455-603

Cockpit Door Assy 171-08455-403 171-08455-607

Cockpit Door Assy 171-08455-601 171-08455-603

Cockpit Door Assy 171-08455-405 171-08455-609

Cockpit Door Assy 190-16461-401 190-16461-625

Cockpit Door Assy 190-16461-601 190-16461-613

Cockpit Door Assy 190-16461-603 190-16461-617

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 14

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

Copyright © 2011 by Embraer S.A. All rights reserved.
DESCRIPTION OLD PN NEW PN

Cockpit Door Assy 190-16461-405 190-16461-621

Cockpit Door Assy 190-16461-605 190-16461-625

Cockpit Door Assy 190-16461-609 190-16461-613

Cockpit Door Assy 190-16461-611 190-16461-617

Cockpit Door Assy 190-16461-403 190-16461-615

Cockpit Door Assy 190-16461-607 190-16461-615

Cockpit Door Assy 190-16461-407 190-16461-623

Cockpit Door Assy 190-17111-401 190-17111-625

Cockpit Door Assy 190-17111-601 190-17111-613

Cockpit Door Assy 190-17111-603 190-17111-617

Cockpit Door Assy 190-17111-405 190-17111-621

Cockpit Door Assy 190-17111-605 190-17111-625

Cockpit Door Assy 190-17111-609 190-17111-613

Cockpit Door Assy 190-17111-611 190-17111-617

Cockpit Door Assy 190-17111-403 190-17111-615

Cockpit Door Assy 190-17111-607 190-17111-615

Cockpit Door Assy 190-17111-409 190-17111-627

Cockpit Door Assy 190-17111-407 190-17111-623

Cockpit Door Assy 190-19435-401 190-19435-603

Cockpit Door Assy 190-19435-403 190-19435-605

Cockpit Door Assy 190-19435-601 190-19435-603

Cockpit Door Assy 190-19435-405 190-19435-607

Cockpit Door Assy 191-10716-401 191-10716-601

Cockpit Door Assy 191-10716-403 191-10716-603

Cockpit Door Assy 191-12848-401 191-12848-601

Cockpit Door Assy 191-12848-403 191-12848-603

Cockpit Door Assy 191-12857-401 191-12857-601

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 15

Copyright © 2011 by Embraer S.A. All rights reserved.
DESCRIPTION OLD PN NEW PN

Cockpit Door Assy 191-12857-403 191-12857-603

Cockpit Door Assy 191-12892-401 191-12892-601

Cockpit Door Assy 191-12892-403 191-12892-603

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

SB No.: 190-52-0038

PAGE: 16

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

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 03 aircraft GROUPS, according to

the relevant configuration and the SB itself is divided into 03 PARTS. The SB

PARTS are featured to allow their independent accomplishment.

REFERENCE APPLICATION TABLE

Aircraft GROUP SB PART APPLICABLE FIGURES

1 I, II and III [1] Figure 1, Figure 2 and Figure 3 [1]

2 II and III [1] Figure 2 and Figure 3 [1]

3 II and III [1] Figure 2 and Figure 3 [1]

1. After the accomplishment of PART II, if applicable, the accomplishment of PART III may be necessary.

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

(1) Replace the cockpit door passive lock striker and quick-release pin with new ones,

according to Figure 1.

C. PART II

(1) Inspect the upper and lower hinges from the cockpit door according to Figure 2.

D. PART III

(1) Replace the upper and lower hinges from the cockpit door and jambs according to

Figure 3.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 17

Copyright © 2011 by Embraer S.A. All rights reserved.
E. Restore the aircraft to normal.

F. Enter the accomplishment 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).

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.: 190-52-0038

PAGE: 18

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

Copyright © 2011 by Embraer S.A. All rights reserved.
1. Remove the cockpit door. Refer to AMM TASK 52-51-01-000-801-A/400 - Cockpit Door

- Removal.

2. Remove and discard striker PN 170-96130-001, shim PN 170-96140-001 and screws

PN MS24693-C5 or PN MS24693-C6 (02 positions).

3. Remove and retain screw PN NAS1132E5 (2 positions) and remove and discard washer

PN NAS1149DN816K (2 positions) from the door frame.

4. Remove and retain pin PN 170-96097-001, washer PN NAS1149D0432K, remove and

discard ring PN MS16624-2025 and quick-release pin PN BLC4BA11SL4A7.

5. Reinstall retained pin PN 170-96097-001 using washer PN NAS1149D0432K (2

positions) and ring PN MS16624-2025.

6. Reinstall the cockpit door. Refer to AMM TASK 52-51-01-400-801-A/400 - Cockpit Door

- Installation.

7. Position striker PN 171-14450-401, using retained screw PN NAS1132E5 (2 positions)

and new washer PN NAS1149DN816K (2 positions), and washer PN MS35338-137 (02

positions) supplied in the kit without completely driving the screws.

8. Install new quick-release pin and then, close the door. After that, manually move the

striker until it touches the passive lock uniformly.

9. Drive the existing Allen screws of the striker until they reach the door frame.

NOTE: The Allen screws are used to adjust the striker.

10.Make sure that the Allen screws are reaching the cockpit door frame, and then, attach

striker PN 171-14450-401 by driving firstly the lower screw PN NAS1132E5 (1 position).

After that, open the door and drive the upper screw PN NAS1132E5 (1 position).

11. Open and close the door to check for interference between the striker and the passive

lock:

(a) If there is no interference, perform step 12.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 19

FIGURE 1 - REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

(SHEET 01 OF 08)

Copyright © 2011 by Embraer S.A. All rights reserved.
(b) If there is any interference, loosen the screws, readjust the striker, and perform step

8 above and on.

12.Close the door, and remove and reinstall the quick-release pin to check for interference

with lanyard cable loop clamp:

(a) If there is no interference, perform step 13.

(b) If there is any interference, adjust laterally the lanyard cable loop clamp, and

perform step 13.

NOTE: The quick-release pin should be freely removed.

13.Reidentify the cockpit door as follows:

(a) Remove and discard the existing placard, according to AMM TASK 20-10-09-000-

801-A/400 - Placards and Markings - Removal.

NOTE: The cockpit door placard can be positioned in one of the places shown in

detail E according to aircraft configuration.

(b) Fill out placard PN 171-08458-001 with the new identification number, as indicated

in paragraph 2.E. REIDENTIFIED PARTS, using a felt-tip pen.

NOTE: Use the information presented in removed placard to fill out the remaining

fields.

(c) Install reidentified placard 171-08458-001, according to AMM TASK 20-10-09-400-

801-A/400 - Placards and Markings - Installation. Refer to Detail E.

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 20

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

FIGURE 1 - REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

(SHEET 02 OF 08)

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

ZONES

221/222

223/224

A

COCKPIT

BULKHEAD

(REF.)

COCKPIT

DOOR

(REF.)

B

D

EM170SB520957A.DGN

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 21

FIGURE 1 - REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

(SHEET 03 OF 08)

Copyright © 2011 by Embraer S.A. All rights reserved.
PRE − MOD

B

2

2

2

C

PASSIVE LOCK

(REF.)

3

4

4

STRIKER

PN 170−96130−001

(REMOVE AND 

DISCARD)

SHIM

PN 170−96140−001

(REMOVE AND 

DISCARD)

SCREW

PN MS24693−C5 OR 

PN MS24693−C6

(REMOVE AND DISCARD)

3

COCKPIT

DOOR FRAME

(REF.)

1

4

WASHER

PN NAS1149D0432K

(REMOVE AND

RETAIN)

RING 

PN MS16624−2025

(REMOVE AND 

DISCARD)

PIN

PN 170−96097−001

(REMOVE AND

RETAIN)

EM170SB520958A.DGN

COCKPIT DOOR 

(REMOVE AND 

RETAIN)

QUICK−RELEASE PIN

PN BLC4BA11SL4A7

(REMOVE AND 

DISCARD)

SCREW

PN NAS1132E5

(REMOVE AND

RETAIN)

WASHER

PN NAS1149DN816K

(1 POSITION)

(REMOVE AND

DISCARD)

SCREW

PN NAS1132E5

(REMOVE AND

RETAIN)

WASHER

PN NAS1149DN816K

(1 POSITION)

(REMOVE AND

DISCARD)

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 22

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

FIGURE 1 - REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

(SHEET 04 OF 08)

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

POST − MOD

C

PASSIVE LOCK

(REF.)

7 10

7 10

7 8 10

DOOR FRAME

(REF.)

8

5

6

WASHER

PN NAS1149D0432K

(REINSTALL)

RING 

PN MS16624−2025

(INSTALL)

5

PIN

PN 170−96097−001

(REINSTALL)

WASHER

PN NAS1149D0432K

ALLEN SCREW (INSTALL) (ADJUST)

9

ALLEN SCREW

(ADJUST)

9

COCKPIT

DOOR 

(REINSTALL)

(OPEN AND CLOSE)

11

8 STRIKER

PN 171−14450−401

(POSITION)

(INSTALL)

NEW QUICK RELEASE

PIN

(INSTALL)

SCREW

PN NAS1132E5

(1 POSITION)

(REINSTALL)

WASHER

PN NAS1149DN816K

(1 POSITION)

WASHER

PN MS35338−137

(1 POSITION)

(INSTALL)

SCREW

PN NAS1132E5

(1 POSITION)

(REINSTALL)

WASHER

PN NAS1149DN816K

(1 POSITION)

WASHER

PN MS35338−137

(1 POSITION)

(INSTALL)

LANYARD CABLE

LOOP CLAMP

(REF.)

12

12

EM170SB520959B.DGN

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 23

FIGURE 1 - REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

(SHEET 05 OF 08)

Copyright © 2011 by Embraer S.A. All rights reserved.
PRE − MOD

FRONT VIEW

FRONT VIEW

POST − MOD

PASSIVE LOCK

(REF.)

STRIKER

PN 170−96130−001

SHIM

PN 170−96140−001

SCREW

PN MS24693−C5 OR 

PN MS24693−C6

(REMOVE AND DISCARD)

4

4

PASSIVE LOCK

(REF.)

STRIKER

PN 171−14450−401

(INSTALL)

EXISITING

ALLEN

SCREWS

(ADJUST)

7

3

C

C

2

5

9

8 10

1

1

STRIKER MUST TOUCH THE PASSIVE LOCK SURFACE.

PIN

PN 170−96097−001

WASHER

PN NAS1149D0432K

(REINSTALL)

WASHER

PN NAS1149D0432K

(INSTALL)

RING 

PN MS16624−2025

(INSTALL)

QUICK RELEASE

PIN

(REMOVE AND

DISCARD)

PIN

PN 170−96097−001

WASHER

PN NAS1149D0432K

(REMOVE AND RETAIN)

RING 

PN MS16624−2025

(REMOVE AND DISCARD)

8

QUICK RELEASE

PIN

(INSTALL)

SCREW

PN NAS1132E5

WASHER

PN NAS1149DN816K

(2 POSITIONS)

(REMOVE AND

RETAIN)

LANYARD CABLE

LOOP CLAMP

(REF.)

12

12

EM170SB520960B.DGN

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 24

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

FIGURE 1 - REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

(SHEET 06 OF 08)

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

DIMENSIONS IN mm

TYPICAL

INSIDE COCKPIT VIEW

1.4

PLACARD

PN 171−08458−001

(REPLACE 

AND REIDENTIFY, AS APPLICABLE)

PLACARD

PN 171−08458−001

(REPLACE 

AND REIDENTIFY, AS APPLICABLE)

80.0

1.0

10.0

D

E

E

13

13

EM170SB520961B.DGN

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 25

FIGURE 1 - REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

(SHEET 07 OF 08)

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

TYPICAL

PLACARD

PN 171−08458−001

(REPLACE AND REIDENTIFY)

13

EM170SB520962B.DGN

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 26

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

FIGURE 1 - REPLACEMENT OF COCKPIT DOOR PASSIVE LOCK STRIKER

(SHEET 08 OF 08)

Copyright © 2011 by Embraer S.A. All rights reserved.
1. Visually check if a shim is installed in the upper and lower hinges assembly of the cockpit

door, according to details B and D, and sections C-C and E-E:

(a) If any discrepancy is detected, perform step 2 below.

(b) If no discrepancy is detected, no additional action is required.

2. Remove the upper and lower hinge, according to AMM TASK 52-51-01-000-802-A/400

- Cockpit Door Hinges - Removal, and inspect if the upper hinge is PN 170-96137-403

and if the lower hinge is PN 170-96133-403 or PN 170-96133-405. Refer to details B and

D, and sections C-C and E-E.

NOTE: The part number is located at the rear side of the hinge.

(a) If any discrepancy is detected, replace the existing upper hinge and lower hinges,

according to PART III of this bulletin.

(b) If no discrepancy is detected, reinstall the removed upper and lower hinges,

according to AMM TASK 52-51-01-400-802-A/400 - Cockpit Door Hinges - Installation.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 27

FIGURE 2 - INSPECTION OF COCKPIT DOOR HINGES

(SHEET 01 OF 03)

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

A

ZONES

221/222

223/224

A

B

C

C

UPPER

HINGE

(REF.)

COCKPIT

DOOR

(REF.)

COCKPIT

BULKHEAD

(REF.)

C−C

UPPER HINGE

PN 170−96137−401

(INSPECT, 

IF APPLICABLE)

SHIM

(INSPECT)

COCKPIT DOOR

ELECTROMECHANICAL

LATCH

D

COCKPIT

DOOR

COCKPIT

BULKHEAD

2

1

EM170SB520983A.DGN

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 28

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

FIGURE 2 - INSPECTION OF COCKPIT DOOR HINGES

(SHEET 02 OF 03)

Copyright © 2011 by Embraer S.A. All rights reserved.
EM170SB520984A.DGN

E

E

SHIM

(INSPECT)

2

1

COCKPIT

DOOR

(REF.)

COCKPIT

BULKHEAD

(REF.)

UPPER

HINGE

(REF.)

E−E

D

LOWER HINGE

PN 170−96133−401 OR

PN 170−96133−403

(INSPECT, 

IF APPLICABLE)

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 29

FIGURE 2 - INSPECTION OF COCKPIT DOOR HINGES

(SHEET 03 OF 03)

Copyright © 2011 by Embraer S.A. All rights reserved.
1. Remove the hinges from the cockpit door jambs as follows:

(a) Remove and discard upper hinge PN 170-96137-401 and retain the existing screws

PN MS27039−0808 (2 positions) from the cockpit door jambs, according to detail B.

Refer to AMM TASK 52-51-01-000-802-A/400 - Cockpit Door Hinges - Removal.

(b) Remove and discard lower hinge PN 170−96133−401 and retain the existing

screws PN NAS1132E3 (2 positions) and washer PN NAS1149DN816K (2 positions) from the cockpit door jambs, according to detail E. Refer to AMM TASK

52-51-01-000-802-A/400 - Cockpit Door Hinges - Removal.

2. Remove the hinges in the in the cockpit door as follows:

(a) Remove and discard upper hinge PN 170-96068-401, spring pin PN PE25041-

055-03 and retain the existing screws PN MS24693C52 (2 positions) from the

cockpit door. Refer to detail B and AMM TASK 52-51-01-000-802-A/400 - Cockpit

Door Hinges - Removal.

(b) Remove and discard lower hinge PN 170-96076-401, spring pin PE25041-055-03

and retain the existing screws MS24693C52 from the cockpit door. Refer to detail

D and AMM TASK 52-51-01-000-802-A/400 - Cockpit Door Hinges - Removal.

3. Install hinges in the in the cockpit door jambs as follows:

(a) Install upper hinge PN 170-96137-403, using retained screw PN MS27039−0808 (2

positions), according to detail B. AMM TASK 52-51-01-400-802-A/400 - Cockpit

Door Hinges - Installation.

(b) Install lower hinge with PN 170-96133-405, using retained screw PN NAS1132E3

(2 positions) and washer PN NAS1149DN816K (2 positions), according to detail E.

Refer to AMM TASK 52-51-01-400-802-A/400 - Cockpit Door Hinges - Installation.

4. Install hinges in the in the cockpit door as follows:

(a) Install upper hinge PN 170-96068-403 and shim PN 171-12687-001, using retained

screw PN MS24693C52 (2 positions) and spring pin PE25041-055-03 wet in

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 30

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

FIGURE 3 - REPLACEMENT OF COCKPIT DOOR AND JAMBS HINGES

(SHEET 01 OF 04)

Copyright © 2011 by Embraer S.A. All rights reserved.
Corrosion Inhibiting Compound (MEP_09-075) COR-BAN 27L , according to

detail C. Refer to AMM TASK 52-51-01-400-802-A/400 - Cockpit Door Hinges -

Installation.

(b) Install lower hinge with PN 170-96076-403 and shim PN 171-12686-001, using

retained screw PN MS24693C52 (2 positions) and spring pin PE25041-055-03 wet

in Corrosion Inhibiting Compound (MEP_09-075) COR-BAN 27L , according to

detail D. Refer to AMM TASK 52-51-01-400-802-A/400 - Cockpit Door Hinges -

Installation.

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 31

FIGURE 3 - REPLACEMENT OF COCKPIT DOOR AND JAMBS HINGES

(SHEET 02 OF 04)

Copyright © 2011 by Embraer S.A. All rights reserved.
EM170SB520971A.DGN

A

ZONES

221/222

223/224

A

B

B

COCKPIT

DOOR

(REF.)

COCKPIT

BULKHEAD

(REF.)

COCKPIT

BULKHEAD

(REF.)

SCREW 

PN MS27039−0808

(2 POSITIONS)

(REUSE)

DOOR

JAMBS 

(REF.)

1 3

UPPER HINGE

PN 170−96137−401

(REMOVE AND DISCARD)

PN 170−96137−403

(INSTALL)

SHIM 2 4 1

PN 171−12687−001

(INSTALL)

UPPER HINGE

PN 170−96068−401

(REMOVE AND DISCARD)

PN 170−96068−403

(INSTALL)

2 4

1

C

D E

COCKPIT

DOOR

(REF.)

C

4

1 3

SCREW

PN MS24693−C52

(2 POSITIONS)

(REUSE)

SPRING PIN

PN PE25041−055−03

(REPLACE)

INSTALL SPRING PIN WET IN SEALANT PN COR−BAN 27L (SPEC. MEP09−075).

SERVICE BULLETIN

SB No.: 190-52-0038

PAGE: 32

DATE: 10/Feb/2011

REVISION No.: 01 - 01/Aug/2011

FIGURE 3 - REPLACEMENT OF COCKPIT DOOR AND JAMBS HINGES

(SHEET 03 OF 04)

Copyright © 2011 by Embraer S.A. All rights reserved.
EM170SB520982A.DGN

SCREW 

PN NAS1132E3

WASHER

PN NAS1149DN816K

(2 POSITIONS)

(REUSE)

DOOR

JAMBS 

(REF.)

1

1

2 4

2 4 1

COCKPIT

DOOR

(REF.)

3

3

LOWER HINGE

PN 170−96076−401

(REMOVE AND DISCARD)

PN 170−96076−403

(INSTALL)

D

E

LOWER HINGE

PN 170−96133−401 

(REMOVE AND DISCARD)

PN 170−96133−405

(INSTALL)

4

SHIM

PN 171−12686−001

(INSTALL)

1

SCREW

PN MS24693−C52

(2 POSITIONS)

(REUSE)

SPRING PIN

PN PE25041−055−03

(REPLACE)

INSTALL SPRING PIN WET IN SEALANT PN COR−BAN 27L (SPEC. MEP09−075).

SERVICE BULLETIN

DATE: 10/Feb/2011

REVISION No.:01 - 01/Aug/2011

SB No.: 190-52-0038

PAGE: 33

FIGURE 3 - REPLACEMENT OF COCKPIT DOOR AND JAMBS HINGES

(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.