# Embraer Service Bulletin 190-24-0019

Copy: Revision 01 ("Embraer Service Information (2)"), 32 pages: PDF https://openairdocs.org/files/sha256/71/ec/71ec3cd1070de9c056482cbe564abcfe302b9af68674b00ec5d6eb522ce84daa; text https://openairdocs.org/service-documents/embraer/sb-190-24-0019/file/71ec3cd1070d.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2010-1161; AD 2011-08-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication.

## Details

- Manufacturer: [Embraer](https://openairdocs.org/service-documents/embraer.md)
- Type: Service bulletin (Service Bulletin)
- Number: 190-24-0019
- Latest revision known: 190-24-0019, Revision 01, dated May 11, 2010 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/embraer/sb-190-24-0019

## ADs that cite it (1) (OpenAirDocs)

Newest first, with the revision each names, as OpenAirDocs read it from the AD's text.

- [AD 2011-08-08](https://openairdocs.org/ad/2011-08-08.md), effective May 18, 2011: Revision 01

## Text (32 pages)

Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2010-1161; AD 2011-08-08 incorporates this document by reference. Not covered by OpenAirDocs’ CC0 dedication. Each page's text from the PDF; open the PDF at a page with #page=N.

### Page 1

1. DESCRIPTION
This sheet transmits Revision 01 to Service Bulletin 190-24-0019.
This is a complete reissue of the Bulletin.
2. ADDITIONAL ACTION
Aircraft that have complied with the previous issue of this bulletin do not need any additional
action.
3. RECORD OF REVISION
Basic issue: 31/Mar/2010.
Revision 01: 11/May/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.C. REASON/ 03 Added reason of Revision 01.
1.G. ESTIMATED MANPOWER/ 06 Updated manpower of test.
3. ACCOMPLISHMENT INSTRUCTIONS/ 10 Removed step 3.D.3) and corrected editorial error.
TRANSMITTAL LETTER
SB No.: 190-24-0019
PAGE: 1 of 1
Embraer Copyright © 2010. All rights reserved.

### Page 2

(No text on this page.)

### Page 3

ELECTRICAL POWER - RAT (RAM AIR TURBINE) - REPLACEMENT OF BALANCE
WASHER SCREWS
1. PLANNING INFORMATION
A. SB EFFECTIVITY
Aircraft affected:
MODEL SN
Embraer 190( ) and 195( ) 19000002, 19000004, 19000006 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, and
19000318 thru 19000347.
Affected component:
The Hamilton Sundstrand Ram Air Turbines (RAT), Model ERPS37T, PN 1703781 Series,
serial numbers: 0101, 0104, 0105, 0106, 0108, 0112, 0115, 0116, 0117, 0118, 0119, 0122,
0125, 0131, 0132, 0134, 0139, 0140, 0142, 0143, 0145, 0146, 0148, 0152, 0155, 0158,
0159, 0161, 0164, 0165, 0166, 0167, 0169, 0170, 0171, 0172, 0173, 0175, 0176, 0177,
0178, 0179, 0181, 0186, 0187, 0188, 0190, 0196, 0198, 0199, 0200, 0201, 0202, 0203,
0204, 0205, 0208, 0209, 0210, 0212, 0213, 0214, 0217, 0218, 0221, 0222, 0223, 0224,
0225, 0226, 0227, 0228, 0229, 0230, 0233, 0234, 0236, 0238, 0240, 0241, 0242, 0243,
0244, 0245, 0246, 0249, 0250, 0251, 0253, 0255, 0256, 0257, 0264, 0265, 0266, 0268,
0272, 0273, 0277, 0279, 0281, 0283, 0285, 0286, 0287, 0288, 0290, 0291, 0293, 0294,
0295, 0299, 0300, 0301, 0302, 0303, 0307, 0308, 0309, 0311, 0313, 0314, 0315, 0316,
0317, 0318, 0319, 0320, 0321, 0322, 0323, 0324, 0326, 0329, 0331, 0333, 0334, 0335,
0336, 0337, 0339, 0340, 0341, 0346, 0347, 0348, 0349, 0350, 0352, 0353, 0364, 0370,
0371, 0374, 0375, 0385, 0386, 0389, 0394, 0412, 0416, 0417, 0424, 0430, 0454, 0467,
0469, 0473, 0474, 0479, 0480, 0481, 0482, 0483, 0484, 0485, 0486, 0487, 0488, 0489,
0490, 0491, 0492, 0493, 0494, 0495, 0496, 0497, 0498, 0499, 0500, 0501, 0502, 0503,
0504, 0505, 0506, 0507, 0508, 0509, 0510, 0511, 0512, 0513, 0514, 0515, 0516, 0517,
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 1 of 27
Embraer Copyright © 2010. All rights reserved.

### Page 4

0518, 0519, 0520, 0521, 0522, 0523, 0524, 0525, 0526, 0527, 0528, 0529, 0530, 0531,
0532, 0533, 0534, 0535, 0536, 0537, 0538, 0539, 0540, 0541, 0542, 0543, 0544, 0545,
0546, 0547, 0548, 0549, 0550, 0551, 0552, 0553, 0554, 0555, 0556, 0557, 0558, 0559,
0560, 0562, 0563, 0564, 0565, 0566, 0567, 0568, 0569, 0570, 0571, 0572, 0573, 0574,
0575, 0576, 0577, 0578, 0579, 0580, 0581, 0582, 0583, 0584, 0585, 0586, 0587, 0588,
0589, 0590, 0591, 0592, 0593, 0594, 0595, 0596, 0597, 0598, 0599, 0600, 0602, 0603,
0604, 0605, 0606, 0607, 0608, 0609, 0610, 0611, 0613, 0614, 0615, 0616, 0617, 0619,
0620, 0621, 0622, 0623, 0624, 0625, 0626, 0628, 0629, 0630, 0631, 0633, 0634, 0636,
0637, 0638, 0639, 0640, 0641, 0642, 0643, 0644, 0645, 0647, 0648, 0649, 0650, 0651,
0652, 0653, 0654, 0655, 0656, 0657, 0658, 0659, 0660, 0661, 0662, 0663, 0664, 0666,
0667, 0668, 0669, 0670, 0671, 0672, 0673, 0674, 0675, 0676, 0677, 0678, 0679, 0681,
0682, 0683, 0684, 0686, 0687, 0688, 0689, 0690, 0691, 0692, 0693, 0695, 0696, 0697,
0698, 0699, 0700, 0701, 0702, 0703, 0704, 0705, 0706, 0707, 0708, 0709, 0710, 0712,
0713, 0714, 0715, 0716, 0717, 0719, and 0720.
NOTE: This effectivity list includes the aircraft originally equipped with the affected
component. Since this component is a “Line Replaceable Unit” (LRU), it may
be necessary to refer to the fleet maintenance control record and verify
whether the unit has been replaced with another one during routine
maintenance.
In-production effectivity:
Embraer 190( ) model aircraft SN 19000348 and on, have an equivalent modification
factory-incorporated.
B. CONCURRENT REQUIREMENTS
None.
C. REASON
(1) HISTORY
Hamilton Sundstrand has discovered that some Ram Air Turbine (RAT)s were
manufactured with nonconforming screws.
Analysis indicated that this nonconformance could be a result of the supplier’s heat
treat process, which increases susceptibility to brittle fracture.
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 2
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 5

(2) OBJECTIVE
To inspect the RAT model, part number and Serial number and, if applicable, to
replace the existing balance screw installed in the unit.
(3) EXPECTED BENEFITS
To return the RAT to its original design configuration.
(4) REVISION HISTORY
REVISION 01: This revision has been issued to update item 1.G. ESTIMATED
MANPOWER, to remove step 3.D.3) and to correct editorial error in
item 3. ACCOMPLISHMENT INSTRUCTIONS.
D. DESCRIPTION
The accomplishment of this bulletin consists in inspecting the Ram Air Turbine (RAT)
model, PN and Serial Number and, if applicable, replacing the balance screw of the
equipment and to reidentify it.
This service bulletin also presents Hamilton Sundstrand SB ERPS37T-24-5, dated March
22/2010, attached to Section 4. APPENDIX 1 , which provides instructions for the
replacement of the balance screw and the re-identification of the RAT.
This Bulletin is divided into 2 PARTS, as follows:
PART I INSPECTION OF RAT MODEL, PART NUMBER AND SERIAL NUMBER
Applicable to: SB EFFECTIVITY
PART I of this bulletin consists in inspecting the Model, PN and serial number of the RAT.
– If the RAT is identified as Model ERPS37T, PN 1703781 Series, serial numbers: 0101,
0104, 0105, 0106, 0108, 0112, 0115, 0116, 0117, 0118, 0119, 0122, 0125, 0131, 0132,
0134, 0139, 0140, 0142, 0143, 0145, 0146, 0148, 0152, 0155, 0158, 0159, 0161,
0164, 0165, 0166, 0167, 0169, 0170, 0171, 0172, 0173, 0175, 0176, 0177, 0178,
0179, 0181, 0186, 0187, 0188, 0190, 0196, 0198, 0199, 0200, 0201, 0202, 0203,
0204, 0205, 0208, 0209, 0210, 0212, 0213, 0214, 0217, 0218, 0221, 0222, 0223,
0224, 0225, 0226, 0227, 0228, 0229, 0230, 0233, 0234, 0236, 0238, 0240, 0241,
0242, 0243, 0244, 0245, 0246, 0249, 0250, 0251, 0253, 0255, 0256, 0257, 0264,
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 3
Embraer Copyright © 2010. All rights reserved.

### Page 6

0265, 0266, 0268, 0272, 0273, 0277, 0279, 0281, 0283, 0285, 0286, 0287, 0288,
0290, 0291, 0293, 0294, 0295, 0299, 0300, 0301, 0302, 0303, 0307, 0308, 0309,
0311, 0313, 0314, 0315, 0316, 0317, 0318, 0319, 0320, 0321, 0322, 0323, 0324,
0326, 0329, 0331, 0333, 0334, 0335, 0336, 0337, 0339, 0340, 0341, 0346, 0347,
0348, 0349, 0350, 0352, 0353, 0364, 0370, 0371, 0374, 0375, 0385, 0386, 0389,
0394, 0412, 0416, 0417, 0424, 0430, 0454, 0467, 0469, 0473, 0474, 0479, 0480,
0481, 0482, 0483, 0484, 0485, 0486, 0487, 0488, 0489, 0490, 0491, 0492, 0493,
0494, 0495, 0496, 0497, 0498, 0499, 0500, 0501, 0502, 0503, 0504, 0505, 0506,
0507, 0508, 0509, 0510, 0511, 0512, 0513, 0514, 0515, 0516, 0517, 0518, 0519,
0520, 0521, 0522, 0523, 0524, 0525, 0526, 0527, 0528, 0529, 0530, 0531, 0532,
0533, 0534, 0535, 0536, 0537, 0538, 0539, 0540, 0541, 0542, 0543, 0544, 0545,
0546, 0547, 0548, 0549, 0550, 0551, 0552, 0553, 0554, 0555, 0556, 0557, 0558,
0559, 0560, 0562, 0563, 0564, 0565, 0566, 0567, 0568, 0569, 0570, 0571, 0572,
0573, 0574, 0575, 0576, 0577, 0578, 0579, 0580, 0581, 0582, 0583, 0584, 0585,
0586, 0587, 0588, 0589, 0590, 0591, 0592, 0593, 0594, 0595, 0596, 0597, 0598,
0599, 0600, 0602, 0603, 0604, 0605, 0606, 0607, 0608, 0609, 0610, 0611, 0613,
0614, 0615, 0616, 0617, 0619, 0620, 0621, 0622, 0623, 0624, 0625, 0626, 0628,
0629, 0630, 0631, 0633, 0634, 0636, 0637, 0638, 0639, 0640, 0641, 0642, 0643,
0644, 0645, 0647, 0648, 0649, 0650, 0651, 0652, 0653, 0654, 0655, 0656, 0657,
0658, 0659, 0660, 0661, 0662, 0663, 0664, 0666, 0667, 0668, 0669, 0670, 0671,
0672, 0673, 0674, 0675, 0676, 0677, 0678, 0679, 0681, 0682, 0683, 0684, 0686,
0687, 0688, 0689, 0690, 0691, 0692, 0693, 0695, 0696, 0697, 0698, 0699, 0700,
0701, 0702, 0703, 0704, 0705, 0706, 0707, 0708, 0709, 0710, 0712, 0713, 0714,
0715, 0716, 0717, 0719, or 0720, the balance screw should be replaced according to
PART II.
– If the RAT is not identified as described above, no action is required.
To gain access to the work area, it is necessary to deploy the RAT located in the RH
forward fuselage bottom, zone 124.
PART II REPLACEMENT OF THE BALANCE SCREW
Applicable to: SB EFFECTIVITY
The modification applicable to PART II of this bulletin consists in replacing the balance
screw of the RAT.
To gain access to the work area, it is necessary to deploy the RAT located in the RH
forward fuselage bottom, zone 124.
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 4
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 7

NOTE: 1) The modification presented in PART I of this bulletin does not affect the
Fatigue Critical Structure (FCS)
2) The modification presented in PART II of this bulletin affects the Fatigue
Critical Structure (FCS); however, no change to the related Damage
Tolerance Inspection (DTI) instructions is required.
E. COMPLIANCE
Refer to paragraph 1.E. Compliance of HS SB ERPS37T-24-5 attached to Section 4.
APPENDIX 1 of this bulletin.
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) PART I - RAT INSPECTION
– Access opening: 0.1 man-hours.
– Inspection: 0.1 man-hours.
– Modification: Not applicable.
– Access closure: Not applicable.
– Test: Not applicable.
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 5
Embraer Copyright © 2010. All rights reserved.

### Page 8

(2) PART II - BALANCE SCREW REPLACEMENT AND REIDENTIFICATION OF RAT
– Access opening: Not applicable.
– Inspection: Not applicable.
– Modification: Refer to paragraph 1.G.Manpower of HS SB ERPS37T-24-5
attached to Section 4. APPENDIX 1 of this bulletin.
– Access closure: 0.2 man-hours.
– Test: 1.G.Manpower of HS SB ERPS37T-24-5 attached to Section 4. APPENDIX
1 of this bulletin.
H. WEIGHT AND BALANCE
None.
I. SOFTWARE ACCOMPLISHMENT SUMMARY
None.
J. REFERENCES
AMM 190/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD
PRACTICES-AIRFRAME.
AMM 190/( ) Aircraft Maintenance Manual PART II - 24-23-00 - ELECTRICAL
POWER.
HS SB
ERPS37T-24-5
EMERGENCY ELECTRICAL POWER - RAM AIR TURBINE -
REPLACE BALANCE WASHER SCREWS.
K. OTHER PUBLICATIONS AFFECTED
None.
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 6
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 9

2. MATERIAL INFORMATION
A. MATERIAL - PRICE AND AVAILABILITY
(1) MATERIAL AVAILABLE FROM EMBRAER
None.
(2) MATERIAL AVAILABLE FROM OTHER VENDORS
Refer to paragraph 2. A. MATERIAL - PRICE AND AVAILABILITY of
HS SB ERPS37T-24-5 attached to Section 4. APPENDIX 1 of this bulletin.
B. INDUSTRY SUPPORT INFORMATION
Refer to paragraph 2. B. INDUSTRY SUPPORT INFORMATION of
HS SB ERPS37T-24-5 attached to Section 4. APPENDIX 1 of this bulletin.
C. MATERIAL NECESSARY FOR EACH AIRCRAFT
Refer to paragraph 2. C. MATERIAL NECESSARY FOR EACH UNIT of
HS SB ERPS37T-24-5 attached to Section 4. APPENDIX 1 of this bulletin.
D. MATERIAL NECESSARY FOR EACH SPARE
Refer to paragraph 2. D. MATERIAL NECESSARY FOR EACH SPARE of
HS SB ERPS37T-24-5 attached to Section 4. APPENDIX 1 of this bulletin.
E. REIDENTIFIED PARTS
Refer to paragraph 2. E. REIDENTIFIED PARTS of HS SB ERPS37T-24-5 attached to
Section 4. APPENDIX 1 of this bulletin.
F. TOOLING - PRICE AND AVAILABILITY
Whenever required, necessary the 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: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 7
Embraer Copyright © 2010. All rights reserved.

### Page 10

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.
4) This Service Bulletin effectivity is divided into 2 PARTS. The SB PARTS are
featured to allow their independent accomplishment.
The steps below outline the general accomplishment instructions.
The detailed sequence is given in SB ERPS37T-24-5 attached to Section 4. APPENDIX 1 of
this bulletin.
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. Deploy the RAT. Refer to AMM TASK 24-23-00-710-801-A/500 - Ram-Air-Turbine (RAT)
Manual Deployment - Operational Test.
C. PART I - RAT INSPECTION
(1) Check the RAT Model, PN and Serial number, as shown in Figure 1.
(a) If the RAT is identified as Model ERPS37T, PN 1703781 Series, serial numbers:
0101, 0104, 0105, 0106, 0108, 0112, 0115, 0116, 0117, 0118, 0119, 0122, 0125,
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 8
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 11

0131, 0132, 0134, 0139, 0140, 0142, 0143, 0145, 0146, 0148, 0152, 0155,
0158, 0159, 0161, 0164, 0165, 0166, 0167, 0169, 0170, 0171, 0172, 0173,
0175, 0176, 0177, 0178, 0179, 0181, 0186, 0187, 0188, 0190, 0196, 0198,
0199, 0200, 0201, 0202, 0203, 0204, 0205, 0208, 0209, 0210, 0212, 0213,
0214, 0217, 0218, 0221, 0222, 0223, 0224, 0225, 0226, 0227, 0228, 0229,
0230, 0233, 0234, 0236, 0238, 0240, 0241, 0242, 0243, 0244, 0245, 0246,
0249, 0250, 0251, 0253, 0255, 0256, 0257, 0264, 0265, 0266, 0268, 0272,
0273, 0277, 0279, 0281, 0283, 0285, 0286, 0287, 0288, 0290, 0291, 0293,
0294, 0295, 0299, 0300, 0301, 0302, 0303, 0307, 0308, 0309, 0311, 0313,
0314, 0315, 0316, 0317, 0318, 0319, 0320, 0321, 0322, 0323, 0324, 0326,
0329, 0331, 0333, 0334, 0335, 0336, 0337, 0339, 0340, 0341, 0346, 0347,
0348, 0349, 0350, 0352, 0353, 0364, 0370, 0371, 0374, 0375, 0385, 0386,
0389, 0394, 0412, 0416, 0417, 0424, 0430, 0454, 0467, 0469, 0473, 0474,
0479, 0480, 0481, 0482, 0483, 0484, 0485, 0486, 0487, 0488, 0489, 0490,
0491, 0492, 0493, 0494, 0495, 0496, 0497, 0498, 0499, 0500, 0501, 0502,
0503, 0504, 0505, 0506, 0507, 0508, 0509, 0510, 0511, 0512, 0513, 0514,
0515, 0516, 0517, 0518, 0519, 0520, 0521, 0522, 0523, 0524, 0525, 0526,
0527, 0528, 0529, 0530, 0531, 0532, 0533, 0534, 0535, 0536, 0537, 0538,
0539, 0540, 0541, 0542, 0543, 0544, 0545, 0546, 0547, 0548, 0549, 0550,
0551, 0552, 0553, 0554, 0555, 0556, 0557, 0558, 0559, 0560, 0562, 0563,
0564, 0565, 0566, 0567, 0568, 0569, 0570, 0571, 0572, 0573, 0574, 0575,
0576, 0577, 0578, 0579, 0580, 0581, 0582, 0583, 0584, 0585, 0586, 0587,
0588, 0589, 0590, 0591, 0592, 0593, 0594, 0595, 0596, 0597, 0598, 0599,
0600, 0602, 0603, 0604, 0605, 0606, 0607, 0608, 0609, 0610, 0611, 0613,
0614, 0615, 0616, 0617, 0619, 0620, 0621, 0622, 0623, 0624, 0625, 0626,
0628, 0629, 0630, 0631, 0633, 0634, 0636, 0637, 0638, 0639, 0640, 0641,
0642, 0643, 0644, 0645, 0647, 0648, 0649, 0650, 0651, 0652, 0653, 0654,
0655, 0656, 0657, 0658, 0659, 0660, 0661, 0662, 0663, 0664, 0666, 0667,
0668, 0669, 0670, 0671, 0672, 0673, 0674, 0675, 0676, 0677, 0678, 0679,
0681, 0682, 0683, 0684, 0686, 0687, 0688, 0689, 0690, 0691, 0692, 0693,
0695, 0696, 0697, 0698, 0699, 0700, 0701, 0702, 0703, 0704, 0705, 0706,
0707, 0708, 0709, 0710, 0712, 0713, 0714, 0715, 0716, 0717, 0719, or 0720,
the balance screw should be replaced according to PART II.
(b) If the Model is not identified as described above, no action is required, and go
to Step 3.E.
D. PART II - BALANCE SCREW REPLACEMENT AND REIDENTIFICATION OF RAT
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 9
Embraer Copyright © 2010. All rights reserved.

### Page 12

1) Replace the balance screw of the RAT as per the instructions presented in item 3.
ACCOMPLISHMENT INSTRUCTIONS of HS SB ERPS37T-24-5 attached to Section
4. APPENDIX 1 of this bulletin.
2) Identify the RAT according to item 3.C. Identification of HS SB ERPS37T-24-5
attached to Section 4. APPENDIX 1 of this bulletin. Refer to Figure 1 of this bulletin.
E. Stow the retraction of the RAT. Refer to AMM TASK 24-23-00-840-801-A/200 -
Ram-Air-Turbine (RAT) - Retraction.
F. Restore the aircraft to normal.
G. 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 to help us improve the quality of the SBs.
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 10
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 13

ZONE
124
A
A
B
C
RAT
IDENTIFICATION
PLATE (REF.)
C
B
SYMBOL "24−5"
(ENGRAVE)
RAT 
(REF.)
PART NO
FAA/PMA
SERIAL NO
DATE OF MFG
AMENDMENT
RAM AIR TURBINE FAA/PMA
24−5
EM170SB240405A.DGN
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 11
FIGURE 1 - IDENTIFICATION OF THE RAM AIR TURBINE (RAT)
(SHEET 01 OF 01)
Embraer Copyright © 2010. All rights reserved.

### Page 14

4. APPENDIX 1
HS SB ERPS37T-24-5 - EMERGENCY ELECTRICAL POWER - RAM AIR TURBINE -
REPLACE BALANCE WASHER SCREWS
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 12
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 15

SERVICE BULLETIN
Original Issue Date: Mar 22/10
 
ERPS37T-24-5
Page 1 of 15
EMERGENCY ELECTRICAL POWER - RAM AIR TURBINE - 
REPLACE BALANCE WASHER SCREWS
© 2010 Hamilton Sundstrand Corporation
PROPRIETARY
 
THIS DOCUMENT AND THE INFORMATION CONTAINED HEREIN ARE THE PROPERTY OF HAMILTON SUNDSTRAND 
CORPORATION (HSC). RECIPIENT AGREES TO HOLD ALL SUCH INFORMATION IN CONFIDENCE AND AGREES IT SHALL BE 
USED ONLY FOR RECIPIENT’S INTERNAL PURPOSES TO MAINTAIN RECIPIENT’S EQUIPMENT OR AS MAY OTHERWISE BE 
PERMITTED IN AN APPLICABLE AGREEMENT BETWEEN RECIPIENT AND HSC. THIS DOCUMENT AND THE INFORMATION 
CONTAINED HEREIN SHALL NOT BE USED FOR ANY OTHER PURPOSE, INCLUDING THE CREATION, MANUFACTURE, 
DEVELOPMENT, OR DERIVATION OF ANY REPAIRS, MODIFICATIONS, SPARE PARTS, DESIGN, OR CONFIGURATION CHANGES, 
OR TO OBTAIN FAA OR ANY OTHER GOVERNMENT OR REGULATORY APPROVAL FOR SAME. RECIPIENT AGREES NOT TO 
DISCLOSE SUCH INFORMATION TO ANY THIRD PARTY, EXCEPT AS MAY OTHERWISE BE PROVIDED FOR IN AN APPLICABLE 
AGREEMENT BETWEEN RECIPIENT AND HSC. COPYING OR DISCLOSURE OF THIS DOCUMENT AND THE INFORMATION 
CONTAINED HEREIN BY ANYONE WITHOUT HSC’S PRIOR WRITTEN PERMISSION IS NOT AUTHORIZED AND MAY RESULT IN 
CRIMINAL AND/OR CIVIL LIABILITY.
Information Subject to Export Control Laws
The technical data in this document (or file) is controlled for export under the Export Administration Regulations (EAR), 
15 CFR Parts 730-774, ECCN: 9E991. Violations of these laws may be subject to fines and penalties under the Export Administration Act.
 
The data in this document were developed only to maintain systems and/or parts manufactured by or for Hamilton Sundstrand or approved 
by Hamilton Sundstrand. The data may not be applicable to any other systems and/or parts, regardless of their apparent similari ty to 
systems and/or parts manufactured by or for Hamilton Sundstrand or approved by Hamilton Sundstrand. Do not rely in any way on data in 
this document to maintain or otherwise support systems and/or parts that were not manufactured by or for Hamilton Sundstrand or approved 
by Hamilton Sundstrand without evidence that the Federal Aviation Administration or other regulatory agency has determined that the data 
in this document is valid for such use.
1. Planning Information
A. Effectivity
The Hamilton Sundstrand Ram Air Turbines (RAT), Model ERPS37T, that are listed below 
and used on Embraer 170 and 190 aircraft. 
Part Number 
Series Serial Numbers
1703781 0101, 0104, 0105, 0106, 0108, 0112, 0115, 0116, 0117, 0118, 0119, 0122, 0125, 
0131, 0132, 0134, 0139, 0140, 0142, 0143, 0145, 0146, 0148, 0152, 0155, 0158, 
0159, 0161, 0164, 0165, 0166, 0167, 0169, 0170, 0171, 0172, 0173, 0175, 0176, 
0177, 0178, 0179, 0181, 0186, 0187, 0188, 0190, 0196, 0198, 0199, 0200, 0201, 
0202, 0203, 0204, 0205, 0208, 0209, 0210, 0212, 0213, 0214, 0217, 0218, 0221, 
0222, 0223, 0224, 0225, 0226, 0227, 0228, 0229, 0230, 0233, 0234, 0236, 0238, 
0240, 0241, 0242, 0243, 0244, 0245, 0246, 0249, 0250, 0251, 0253, 0255, 0256, 
0257, 0264, 0265, 0266, 0268, 0272, 0273, 0277, 0279, 0281, 0283, 0285, 0286, 
0287, 0288, 0290, 0291, 0293, 0294, 0295, 0299, 0300, 0301, 0302, 0303, 0307, 
0308, 0309, 0311, 0313, 0314, 0315, 0316, 0317, 0318, 0319, 0320, 0321, 0322, 
0323, 0324, 0326, 0329, 0331, 0333, 0334, 0335, 0336, 0337, 0339, 0340, 0341, 
(continued on the next page)
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 13
Embraer Copyright © 2010. All rights reserved.

### Page 16

Original Issue Date: Mar 22/10 ERPS37T-24-5Page 2
SERVICE BULLETIN 
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
B. Concurrent Requirements
None.
C. Reason
Hamilton Sundstrand has discovered that RATs were manufactured with nonconforming 
screws. To date, there have been five instances of a fractured balance washer screw on 
multiple RAT part number configurations. Fracture of a balance washer screw can result in 
the loss of the associated balance washer and create an unacceptable turbine imbalance. 
Inspection of other screws in Hamilton Sundstrand stock revealed metallographic 
nonconformities consistent with those of the fractured screws. The suspect screws have 
been isolated to a lot from a specific supplier. Analysis indicates the nonconformance could 
be a result of the supplier’s heat treat process, which increases susceptibility to brittle 
fracture. Replacement of the suspect screws with confirmed conforming screws will 
eliminate potential loss of a balance washer. Incorporation of this bulletin will ensure that 
the RAT balance washer screws conform to specification.
Part Number 
Series Serial Numbers
1703781 (continued from the previous page)  
0346, 0347, 0348, 0349, 0350, 0352, 0353, 0364, 0370, 0371, 0374, 0375, 0385, 
0386, 0389, 0394, 0412, 0416, 0417, 0424, 0430, 0454, 0467, 0469, 0473, 0474, 
0479, 0480, 0481, 0482, 0483, 0484, 0485, 0486, 0487, 0488, 0489, 0490, 0491, 
0492, 0493, 0494, 0495, 0496, 0497, 0498, 0499, 0500, 0501, 0502, 0503, 0504, 
0505, 0506, 0507, 0508, 0509, 0510, 0511, 0512, 0513, 0514, 0515, 0516, 0517, 
0518, 0519, 0520, 0521, 0522, 0523, 0524, 0525, 0526, 0527, 0528, 0529, 0530, 
0531, 0532, 0533, 0534, 0535, 0536, 0537, 0538, 0539, 0540, 0541, 0542, 0543, 
0544, 0545, 0546, 0547, 0548, 0549, 0550, 0551, 0552, 0553, 0554, 0555, 0556, 
0557, 0558, 0559, 0560, 0562, 0563, 0564, 0565, 0566, 0567, 0568, 0569, 0570, 
0571, 0572, 0573, 0574, 0575, 0576, 0577, 0578, 0579, 0580, 0581, 0582, 0583, 
0584, 0585, 0586, 0587, 0588, 0589, 0590, 0591, 0592, 0593, 0594, 0595, 0596, 
0597, 0598, 0599, 0600, 0602, 0603, 0604, 0605, 0606, 0607, 0608, 0609, 0610, 
0611, 0613, 0614, 0615, 0616, 0617, 0619, 0620, 0621, 0622, 0623, 0624, 0625, 
0626, 0628, 0629, 0630, 0631, 0633, 0634, 0636, 0637, 0638, 0639, 0640, 0641, 
0642, 0643, 0644, 0645, 0647, 0648, 0649, 0650, 0651, 0652, 0653, 0654, 0655, 
0656, 0657, 0658, 0659, 0660, 0661, 0662, 0663, 0664, 0666, 0667, 0668, 0669, 
0670, 0671, 0672, 0673, 0674, 0675, 0676, 0677, 0678, 0679, 0681, 0682, 0683, 
0684, 0686, 0687, 0688, 0689, 0690, 0691, 0692, 0693, 0695, 0696, 0697, 0698, 
0699, 0700, 0701, 0702, 0703, 0704, 0705, 0706, 0707, 0708, 0709, 0710, 0712, 
0713, 0714, 0715, 0716, 0717, 0719, 0720
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 14
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 17

SERVICE BULLETIN
Original Issue Date: Mar 22/10
 
ERPS37T-24-5
Page 3
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
D. Description
This bulletin gives instructions to replace the balance washer screws and identify the RAT.
 
For a RAT with a missing balance washer, or with a balance washer screw that cannot be 
removed in its entirety, instructions are also given to disassemble the RAT as necessary to 
remove the fractured screw and balance washer, balance the turbine assembly, assemble 
the RAT, and test the RAT.
E. Compliance
Incorporation of this service bulletin is to be accomplished at the earliest opportunity.
F. Approval
Government or other regulatory agency approval of the bulletin is the responsibility of 
Embraer. 
 
Embraer has reviewed and approved this document.
G. Manpower
A maximum of 0.5 man-hour will be required to replace the balance washer screws and 
identify the RAT. 
 
For a RAT with a missing balance washer, or with a balance washer screw that cannot be 
removed in its entirety, a maximum of 8.0 man-hours will be required to disassemble the 
RAT as necessary to remove the fractured screw and balance washer, balance the turbine 
assembly, assemble the RAT, and test the RAT.
H. Weight and Balance
None.
I. Electrical Load Data
Not applicable.
J. Software Accomplishment Summary
Not applicable.
K. References
Applicable Aircraft Maintenance Manual (AMM), Hamilton Sundstrand Component 
Maintenance Manual (CMM) 24-23-60, Hamilton Sundstrand Standard Practices Manual 
(SPM) 20-00-00, and Embraer Service Bulletins 170-24-0048 and 190-24-0019. 
L. Other Publications Affected
Hamilton Sundstrand CMM 24-23-60 will be revised to incorporate this service bulletin.
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 15
Embraer Copyright © 2010. All rights reserved.

### Page 18

Original Issue Date: Mar 22/10 ERPS37T-24-5Page 4
SERVICE BULLETIN 
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
M. Interchangeability or Intermixability of Parts
Not affected. 
2. Material Information
A. Material - Price and Availability
(1) Hamilton Sundstrand will supply the replacement parts required for accomplishment of 
this bulletin on a no-charge basis until March 21, 2012. The replacement parts are 
currently available in limited quantities (refer to Table 1 of this bulletin for the parts 
breakdown). Operators approved by Hamilton Sundstrand to perform the modification 
of units at their facility should place a single “no-charge” order to Hamilton Sundstrand. 
Operators can forward these orders to their assigned Hamilton Sundstrand 
Commercial Spares Administrator (or fax to +1-815-226-2624, if the responsible 
Administrator is not known). In addition, operators can also use the Hamilton 
Sundstrand website at www.hamiltonsundstrand.com to contact the Commercial 
Spares group. Upon entering the website, select “Customer Service” followed by 
“Commercial Spares” for other contact and order processing options that are available. 
Orders must clearly reference fleet requirements, noting the bulletin number, serial 
numbers of affected units, total quantity of parts, and anticipated incorporation 
schedule. Hamilton Sundstrand will acknowledge the operator order with an 
established delivery rate.
B. Industry Support Information
(1) Hamilton Sundstrand will also give the following:
(a) A maximum labor allowance of 0.5 man-hour multiplied by the operator's current 
approved hourly rate for accomplishment of this service bulletin in the shop. The 
labor allowance will expire March 21, 2012.
(b) A maximum labor allowance of 0.5 man-hour multiplied by the operator's current 
approved hourly rate for replacement of the balance washer screws on the aircraft 
(refer to Embraer Service Bulletin 170-24-0048 or 190-24-0019). The labor 
allowance will expire March 21, 2012.
(c) If removal from the aircraft is required, a maximum labor allowance of 6.0  man-
hours multiplied by the operator's current approved hourly rate for replacement of 
the RAT on the aircraft and test on wing (refer to Embraer Service 
Bulletin 170-24-0048 or 190-24-0019). The labor allowance will expire 
March 21, 2012.
(d) Operators should forward a claim for labor reimbursement to their assigned 
Hamilton Sundstrand Rockford Warranty Administrator. If the responsible 
Administrator is not known, the claim should be mailed to Warranty 
Administration, 4747 Harrison Ave, Rockford, IL 61126, USA, MS 106-6. The 
claim should reference the service bulletin number, serial numbers modified, date 
modified, total hours, and approved labor rate.
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 16
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 19

SERVICE BULLETIN
Original Issue Date: Mar 22/10
 
ERPS37T-24-5
Page 5
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
(2) For units with a missing balance washer, or with a balance washer screw that cannot 
be removed in its entirety, Hamilton Sundstrand will incorporate this modification into 
returned units at no charge until March 21, 2012. Contact Hamilton Sundstrand at the 
address that follows for scheduling information: 
 
Hamilton Sundstrand 
4747 Harrison Avenue 
P.O. Box 7002 
Rockford, IL 61125-7002 
Attention: Repair Administration 
Mail Stop 151-6 
Telephone: +1-815-226-6849 
Fax: 815-394-2414
C. Material Necessary For Each Unit
(1) Material to be Purchased
Table 1
New Parts Necessary
Table 1 Note 1: Operators should order a quantity of 10 screws for each unit for incorporation of 
this bulletin.
Table 1 Note 2: Hamilton Sundstrand will supply the noted part at no charge (refer to paragraph 
2.A. of this bulletin). 
(2) Material Supplied by the Operator
(a) None. 
D. Material Necessary For Each Spare
(1) The same as the material necessary for each unit.
E. Reidentified Parts
(1) Refer to paragraph 3.C. of this bulletin.
F. Tooling - Price and Availability 
(1) No tooling other than that required for shop maintenance of the RAT is required to do 
this modification.
New 
Part Number Nomenclature
Old 
Part Number Qty Unit Price
Disposition 
Instructions
Same Screw MS24667-14 AR
(Note 1)
(Note 2) Remove suspect 
old screws, install 
new conforming 
screws
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 17
Embraer Copyright © 2010. All rights reserved.

### Page 20

Original Issue Date: Mar 22/10 ERPS37T-24-5Page 6
SERVICE BULLETIN 
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
3. Accomplishment Instructions
A. General
CAUTION: THE RAT CONTAINS DESIGN CRITICAL CHARACTERISTICS, 
PROCESSES, AND PROCEDURES. THE DESIGN CRITICAL 
CHARACTERISTICS ARE IDENTIFIED WITH THE SYMBOL >>DCC<<. 
REFER TO THE INTRODUCTION SECTION OF CMM 24-23-60 FOR A 
COMPLETE EXPLANATION OF DESIGN CRITICAL CHARACTERISTICS.
(1) The user should obtain the material safety data sheets [Occupational Safety and 
Health Act (OSHA) Form 20 or equivalent] from the manufacturers or suppliers of 
materials to be used. The user must become completely familiar with the manufacturer/
supplier information and adhere to the procedures, recommendations, warnings, and 
cautions of the manufacturer/supplier for the safe use, handling, storage, and disposal 
of these materials. The user should also read the long version of the warnings 
contained in this service bulletin. The long version warnings are contained in Hamilton 
Sundstrand Warnings Registry 341-006 available free of charge to all organizations 
that are on distribution for this Service Bulletin. The Warnings Registry 341-006 is also 
available at www.hsvas.com.
B. Modification
(1) If the RAT is installed on the aircraft, make sure the RAT is deployed (refer to the 
applicable AMM).
CAUTION: THE RAT TURBINE BLADES SHOULD BE PROTECTIVELY COVERED 
DURING BALANCE WASHER SCREW REMOVAL AND INSTALLATION. 
THE BLADES CAN BE EASILY DAMAGED. 
(2) Install a protective covering on the RAT turbine blades to prevent damage to the blades 
from contact with the tooling or screws. 
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 18
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 21

SERVICE BULLETIN
Original Issue Date: Mar 22/10
 
ERPS37T-24-5
Page 7
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
(3) Rotate the turbine assembly and do a check for missing balance washers (refer to the 
items that follow): 
-  Balance washers (360, -360A, -360B, or -360C, IPL Figure 2, CMM 24-23-60), 
(370 or -370A), and (-375).
NOTE: The number of balance washers installed will vary according to the 
magnitude of the imbalance that existed before the turbine assembly was 
balanced. 
- The threaded holes around the turbine circumference that are not used for 
balance washers have a set screw installed. The set screw is secured 
using a 5/64-inch internal hex tool. The set screws should not be removed 
or replaced.
- The threaded holes around the turbine circumference with balance 
washers installed, use a countersunk socket head cap screw 
MS24667-14 to secure the washers [refer to screw (380)]. 
NOTE: Missing balance washers are evidenced by the remaining screw and primer 
residue (in a rectangular or circular shaped pattern) on the turbine assembly 
(refer to Figure 1 of this bulletin). 
(4) If any balance washers are missing (because of a fractured screw), do the steps that 
follow:
NOTE: If the RAT is installed on the aircraft, it must be removed from the aircraft 
(refer to the applicable AMM) for removal of the fractured screw and to 
balance the turbine assembly. The RAT must either be returned to Hamilton 
Sundstrand or to a repair facility that has the capability to disassemble, 
repair, balance, and test the RAT. 
(a) Report any occurrences of a fractured screw to Hamilton Sundstrand as follows:  
 
Greg Kuczek 
Hamilton Sundstrand Service Engineering  
Phone: +1- 815-226-6581 
Fax: +1-860-660-4995 
E-Mail: gregory.kuczek@hs.utc.com
(b) Disassemble the RAT (refer to CMM 24-23-60, DISASSEMBLY) as necessary to 
remove the following parts and to get access to the fractured screw.
- Balance washers (360, -360A, -360B, or -360C, IPL Figure 2, CMM 24-23-60), 
(370 or -370A), and (-375)
- Screws (380)
NOTE: Some screws, depending on how near they are to a turbine blade, can 
not be extracted unless the turbine blades are disassembled from the 
turbine assembly. In those cases, the RAT must be disassembled as 
necessary to remove the screw.
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 19
Embraer Copyright © 2010. All rights reserved.

### Page 22

Original Issue Date: Mar 22/10 ERPS37T-24-5Page 8
SERVICE BULLETIN 
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
(c) Use a screw extractor (or equivalent) to remove the remaining portion of the 
fractured screw. Make sure no filings or fragments enter the turbine assembly. Do 
not use heat or fluid to remove the screw.
(d) Do a visual check of the self-locking screw thread insert to make sure there is no 
mechanical damage.
(e) Assemble the turbine assembly as necessary (refer to CMM 24-23-60, 
ASSEMBLY).
(f) Remove the protective covering from the turbine blades.
(g) Balance the turbine assembly (refer to CMM 24-23-60, ASSEMBLY).
(h) Assemble the RAT as necessary (refer to CMM 24-23-60, ASSEMBLY).
(i) Do a test of the RAT (refer to 24-23-60, TESTING AND FAULT ISOLATION).
(j) After all of the balance washer screws have been replaced, identify the RAT as 
follows (refer to SPM 20-00-00, ASSEMBLY): 
1 Put the symbol 24-5 in the AMENDMENT block of the identification plate 
(380, IPL Figure 1, CMM 24-23-60).
(k) Proceed to paragraph 3.E. of this bulletin. 
CAUTION: REPLACE THE BALANCE WASHER SCREWS ONE AT A TIME. DO NOT 
REMOVE ALL OF THE SCREWS AT THE SAME TIME. IF MORE THAN ONE 
SCREW IS REMOVED AT A TIME, THE TURBINE ASSEMBLY MUST BE RE-
BALANCED.
(5) If no balance washers are missing, do the steps that follow to replace the balance 
washer screws (one at a time):
(a) For each balance washer that is unsymmetrical in shape, use a suitable 
temporary marking method (tape, indelible ink, or equivalent) to mark the radial 
orientation of the installed balance washer. The original installed radial orientation 
of the washer must be maintained. 
NOTE: If a balance washer is circular in shape, it is not necessary to mark its 
radial orientation.
(b) Do one of the steps that follow: 
1 If the RAT is installed on the aircraft, rotate the turbine assembly until the 
balance washer is positioned in a manner to minimize the potential for the 
balance washer to fall out (when the associated screw is removed).
2 If the RAT is off the aircraft, position the unit to access the balance washer 
facing up. 
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 20
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 23

SERVICE BULLETIN
Original Issue Date: Mar 22/10
 
ERPS37T-24-5
Page 9
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
CAUTION: DO NOT USE A WORN INTERNAL HEX TOOL WITH ROUNDED 
CORNERS TO REMOVE THE SCREW. IF A WORN TOOL IS USED, 
THE POTENTIAL EXISTS FOR STRIPPING THE SOCKET HEAD OF 
THE SCREW. 
CAUTION: USE CARE NOT TO DAMAGE EITHER THE BALANCE WASHER OR 
TURBINE ASSEMBLY IF IT IS NECESSARY TO STRIKE THE HEAD OF 
THE SCREW BECAUSE THE BREAK-AWAY TORQUE IS EXCESSIVE. 
(c) While holding the balance washer in place, use a 3/32-inch internal hex tool to 
remove one screw from one balance washer.
NOTE: The use of a hex insert bit is preferred. 
NOTE: If the screw break-away torque is excessive, it is permissible to lightly 
strike the head of the screw using a small hammer and a 5/16-inch 
(8-millimeter) pin punch. It should not be necessary to strike more than 
two times. 
(d) If the screw is fractured (with the balance washer installed) or if a screw fractures 
during removal, do the steps that follow to remove the remaining portion of the 
screw: 
1 Report any occurrences of a fractured screw to Hamilton Sundstrand as 
follows: 
 
Greg Kuczek 
Hamilton Sundstrand Service Engineering  
Phone: +1- 815-226-6581 
Fax: +1-860-660-4995 
E-Mail: gregory.kuczek@hs.utc.com
2 If the remaining portion of the fractured screw is protruding above the turbine 
surface, do the steps that follow: 
a Apply protective tape on the turbine (in the area of the screw) to prevent 
surface damage during the removal attempt. 
b Use pliers, a vice grip, or an equivalent gripping tool to remove the 
screw.
c Remove the protective tape from the turbine. 
d If the screw is removed in its entirety, proceed to step 3.B.(5)(e) of this 
bulletin.
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 21
Embraer Copyright © 2010. All rights reserved.

### Page 24

Original Issue Date: Mar 22/10 ERPS37T-24-5Page 10
SERVICE BULLETIN 
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
3 If the remaining portion of the screw is flush or below the turbine surface, or 
if the screw can not be removed in its entirety, do the steps that follow: 
NOTE: If the RAT is installed on the aircraft, Hamilton Sundstrand 
recommends the RAT be removed from the aircraft (refer to the 
applicable AMM) for removal of the fractured screw. The RAT 
should either be returned to Hamilton Sundstrand or to a repair 
facility that has the capability to disassemble, repair, balance, and 
test the RAT.  
 
However, as an option, and at the operator's discretion, an attempt 
to mechanically extract a screw while the RAT is installed on the 
aircraft is allowed.  
 
The procedure to mechanically extract a fractured screw, or one 
with a stripped socket head, must not use any heat or fluid. Care 
must be taken to make sure no filings or fragments enter the 
turbine assembly.  
 
The turbine hub and turbine blades should be protectively covered 
to prevent mechanically induced damage during the extraction 
procedure. 
 
The self-locking screw thread insert should be visually inspected 
(after the screw is extracted) to make sure there is no mechanical 
damage. 
a For RATs removed from the aircraft, disassemble the RAT (refer to 
CMM 24-23-60, DISASSEMBLY) as necessary to get access to the 
fractured screw.
NOTE: Some screws, depending on how near they are to a turbine 
blade, can not be extracted unless the turbine blades are 
disassembled from the turbine assembly. In those cases, the 
RAT must be disassembled as necessary to remove the 
screw.
b Use a screw extractor (or equivalent) to remove the remaining portion 
of the fractured screw. Make sure no filings or fragments enter the 
turbine assembly. Do not use heat or fluid to remove the screw. 
NOTE: If the RAT is installed on the aircraft, and the screw can not 
be extracted, the RAT must be removed from the aircraft 
(refer to the applicable AMM) and disassembled as 
necessary to remove the fractured screw. The RAT should 
either be returned to Hamilton Sundstrand or to a repair 
facility that has the capability to disassemble, repair, balance, 
and test the RAT. 
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 22
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 25

SERVICE BULLETIN
Original Issue Date: Mar 22/10
 
ERPS37T-24-5
Page 11
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
c Do a visual check of the self-locking screw thread insert to make sure 
there is no mechanical damage.
4 If disassembly of the turbine assembly was not required to remove the 
fractured screw, proceed to step 3.B.(5)(e) of this bulletin.
5 For RATs removed from the aircraft, if disassembly of the turbine assembly 
was required to remove the fractured screw, do the following: 
a Remove the remaining screws (380, IPL Figure 2, CMM 24-23-60) and 
the following balance washers:
- Balance washers (360, -360A, -360B, or -360C), (370 or -370A), and 
(-375)
b Assemble the turbine assembly as necessary (refer to CMM 24-23-60, 
ASSEMBLY).
c Remove the protective covering from the RAT turbine blades.
d Balance the turbine assembly (refer to CMM 24-23-60, ASSEMBLY).
e Assemble the RAT as necessary (refer to CMM 24-23-60, 
ASSEMBLY).
f Do a test of the RAT (refer to CMM 24-23-60, TESTING AND FAULT 
ISOLATION).
g After all of the balance washer screws have been replaced, identify the 
RAT as follows (refer to SPM 20-00-00, ASSEMBLY):
1) Put the symbol 24-5 in the AMENDMENT block of the identification 
plate (380, IPL Figure 1, CMM 24-23-60).
h Proceed to paragraph 3.E. of this bulletin. 
(e) If the balance washer inadvertently falls off after the screw is removed, install the 
balance washer in its original installed orientation, as determined from the 
marking method used in step 3.B.(5)(a) of this bulletin. 
(f) While holding the balance washer in place, install a new screw MS24667-14. 
Torque the screw 16 to 20 pound inches (1.9 to 2.2 Newton meters). 
NOTE: It is not necessary to remove the existing primer residue or apply new 
primer if the balance washer inadvertently fell off after the screw was 
removed. 
(g) Use a suitable temporary marking method (tape, indelible ink, or equivalent) to 
mark the location where the balance washer screw has been replaced.
(h) Repeat steps 3.B.(5)(b) through (g) of this bulletin for each balance washer screw. 
(i) Record the total number of replaced screws. 
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 23
Embraer Copyright © 2010. All rights reserved.

### Page 26

Original Issue Date: Mar 22/10 ERPS37T-24-5Page 12
SERVICE BULLETIN 
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
(j) Remove any tape (that was used to mark the orientation of the installed balance 
washers or the locations where the screws had been replaced).
(k) Remove the protective covering from the RAT turbine blades.
(6) After all of the balance washer screws have been replaced, identify the RAT as follows 
(refer to SPM 20-00-00, ASSEMBLY):
(a) Put the symbol 24-5 in the AMENDMENT block of the identification plate (380, 
IPL Figure 1, CMM 24-23-60).
(7) If the RAT is installed on the aircraft, make sure the RAT is re-stowed (refer to the 
applicable AMM).
C. Identification
NOTE: After all of the balance washer screws have been replaced, the RAT is identified 
by adding the symbol 24-5 in the AMENDMENT block of the identification plate.
D. Test
(1) For units in the shop (if no balance washers were found missing, disassembly of the 
turbine was not required, and the balance washer screws were replaced one screw at 
a time), a test of the RAT is optional based on operator experience, normal shop 
practices, and reason for removal (refer to CMM 24-23-60, TESTING AND FAULT 
ISOLATION).
E. Return Balance Washer Screws to Hamilton Sundstrand
(1) If the unit had a missing balance washer or a fractured screw, return all of the removed 
screws (including the remnants of the fractured screw) to Hamilton Sundstrand for 
further investigation as follows: 
(a) Put the screws in a mailing package. 
(b) Tag the screws (or include a note) to identify the part number and serial number 
of the RAT the screws were removed from and to identify the applicable aircraft 
MSN. 
(c) Return the screws with the applicable RAT part number, RAT serial number, and 
aircraft MSN to the address that follows: 
 
Hamilton Sundstrand Service Engineering 
4747 Harrison Avenue 
P.O. Box 7002 
Rockford, IL 61125-7002 
Attention: Greg Kuczek 
Phone: +1- 815-226-6581 
Fax: +1-860-660-4995 
E-Mail: gregory.kuczek@hs.utc.com
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 24
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 27

SERVICE BULLETIN
Original Issue Date: Mar 22/10
 
ERPS37T-24-5
Page 13
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
F. Notification of Completion Form
(1) Do the following upon completion of this service bulletin:  
(a) Make a copy of the “Notification of Completed SB ERPS37T-24-5” form (refer to 
Table 2 of this bulletin), complete the form, and fax the completed form to 
Hamilton Sundstrand as follows: 
 
Hamilton Sundstrand Corporation 
Retrofit Management Group 
Fax: +1-860-998-3695
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 25
Embraer Copyright © 2010. All rights reserved.

### Page 28

Original Issue Date: Mar 22/10 ERPS37T-24-5Page 14
SERVICE BULLETIN 
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
Figure 1
Missing Balance Washer
SB-ERPS37T245-104620
SERVICE BULLETIN
SB No.: 190-24-0019
PAGE: 26
DATE: 31/Mar/2010
REVISION No.: 01 - 11/May/2010
Embraer Copyright © 2010. All rights reserved.

### Page 29

SERVICE BULLETIN
Original Issue Date: Mar 22/10
 
ERPS37T-24-5
Page 15
Hamilton Sundstrand Proprietary - Use or disclosure of this data is subject to restrictions on the title page of this document.
Table 2
Notification of Completion Form
NOTIFICATION OF COMPLETED SB ERPS37T-24-5
“Replace Balance Washer Screws”
SENT FROM: 
Sender Name: 
Sender Company: 
Aircraft Operator:  
Sender Fax #: 
Send Date:
**PLEASE SUBMIT THIS NOTIFICATION SHEET WITHIN 10 DAYS AFTER MODIFICATION** 
SEND TO: 
 
Hamilton Sundstrand Corporation 
Retrofit Management Group 
Fax: +1-860-998-3695 
RAT
Serial Number
Aircraft MSN 
or Tail Number
 Bulletin 
Completion Date
Number 
of Replaced 
Screws
Comments
SERVICE BULLETIN
DATE: 31/Mar/2010
REVISION No.:01 - 11/May/2010
SB No.: 190-24-0019
PAGE: 27
Embraer Copyright © 2010. All rights reserved.

### Page 30

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### Page 31

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.

### Page 32

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