1. DESCRIPTION

This sheet transmits Revision 02 to Service Bulletin 500-55-A004.

This is a complete reissue of the Service Bulletin.

This revision incorporates the information presented in the Information Notice related to the

previous issues of this Service Bulletin, as listed below:

None.

2. ADDITIONAL ACTION

Aircraft that have complied with the previous issue of this service bulletin do not need any

additional action.

3. RECORD OF REVISION

Basic issue: 21/Jul/2014

Revision 01: 24/Jul/2014

Revision 02: 25/Jul/2014

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 Added aircraft to the SB effectivity.

1.C. REASON / 02 Added reason for Revision 02.

1.E. COMPLIANCE / 03 Changed the Compliance.

3. ACCOMPLISHMENT INSTRUCTIONS

Page 8 Editorial change.

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TRANSMITTAL LETTER

SB No.: 500-55-A004

PAGE: 1 of 1

Copyright © 2014 by Embraer S.A. All rights reserved.
STABILIZERS - INSPECTION AND REPLACEMENT OF THE BARREL SELF-LOCKING

NUT

In connection with the use of this document, Embraer does not provide any express or implied

warranties and expressly disclaims any warranty of merchantability or fitness for a particular purpose.

1. PLANNING INFORMATION

A. SB EFFECTIVITY

(1) PART I: INSPECTION OF BARREL SELF-LOCKING NUTS

Aircraft affected:

MODEL SN

EMB-500 ’Phenom 100’ 50000218 thru 50000333, 50000336, 50000337,

50000339, and 50000341.

(2) PART II: REPLACEMENT OF THE BARREL SELF-LOCKING NUT

Aircraft affected:

MODEL SN

EMB-500 ’Phenom 100’ 50000218 thru 50000333, 50000336, 50000337,

50000339, and 50000341.

In-production effectivity:

The subject presented in this bulletin does not affect any in-production aircraft.

B. CONCURRENT REQUIREMENTS

None.

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ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 1 of 18

Copyright © 2014 by Embraer S.A. All rights reserved.
C. REASON

(1) HISTORY

At the assembly line, during and inspection on the horizontal stabilizer-to-vertical

stabilizer attachment, barrel self-locking nuts with cracks have been found. The

investigation determined that the cracks were a result of hydrogen embrittlement and

related to the nut manufacturing process. Embraer is working with the barrel

self-locking nuts supplier to identify the affected batch.

(2) OBJECTIVE

To inspect the barrel self-locking nuts of the horizontal stabilizer-to-vertical stabilizer

attachment and replace them, as necessary.

(3) EXPECTED BENEFITS

The inspection is aimed at preventing that defective barrel self-locking nuts remain

installed, which can affect the integrity of the horizontal stabilizer-to-vertical stabilizer

attachment.

(4) REVISION HISTORY

Revision 01.

– Changed the Compliance.

Revision 02.

– This revision is issued to add aircraft SN 50000218 thru SN 50000238 to the

service bulletin effectivity.

– Changed the Compliance.

D. DESCRIPTION

(1) PART I: INSPECTION OF BARREL SELF-LOCKING NUTS

The modification presented in PART I of this service bulletin consists of inspecting

the installed barrel self-locking nuts. If one or more barrel self-locking nut is of the

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SERVICE BULLETIN

ALERT

ALERT SB No.: 500-55-A004

PAGE: 2

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

Copyright © 2014 by Embraer S.A. All rights reserved.
same type shown in Figure 1 C2, NOT ACCEPTABLE and 4. APPENDIX 1, replace

it/them as given in PART II.

For removed nuts, fill up the table given in 4. APPENDIX 2 with the requested

information, send it and contact Embraer Technical Support Department through

contact.center@embraer.com.

(2) PART II: REPLACEMENT OF THE BARREL SELF-LOCKING NUT

The modification presented in PART II of this service bulletin consists of replacing

the defective barrel self-locking nut.

E. COMPLIANCE

This Service Bulletin must be accomplished before next flight.

F. APPROVAL

The technical aspects of this Service Bulletin are approved by: Embraer - Engineering

Board.

G. COMMUNICATIONS TO EMBRAER

EMBRAER requests that any results found during these inspections be informed to your

local EMBRAER representatives or offices.

H. REFERENCES

AMM 500/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD

PRACTICES-AIRFRAME.

AMM 500/( ) Aircraft Maintenance Manual PART II - 55-32-23 - STABILIZERS.

SRM 500/( ) Structural Repair Manual Part II - 51-21-05, 51-22-01, and 51-22-

03 - STANDARD PRACTICES AND STRUCTURES - GENERAL.

I. PUBLICATIONS AFFECTED

None.

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SERVICE BULLETIN

ALERT

ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 3

Copyright © 2014 by Embraer S.A. All rights reserved.
2. MATERIAL INFORMATION

A. MATERIAL - PRICE AND AVAILABILITY

None.

B. INDUSTRY SUPPORT INFORMATION

(1) WARRANTY COVERAGE

(a) Parts

The SB parts will be provided at no charge.

(b) Labor

Embraer will compensate 2.5 man-hours for the service bulletin PART I

incorporation if it is performed in an Embraer-authorized service center

NOTE: If barrel self-locking nut replacement is necessary, there will be an

additional 0.5 man-hours per nut.

(c) Expiration

Within the next 30 days.

C. MATERIAL NECESSARY FOR EACH AIRCRAFT

The expendable or consumable parts presented in the AMM Tasks referred to in this

bulletin, which are necessary for its accomplishment, should be procured from the

operator’s inventories or ordered as spares.

(1) MATERIAL TO BE PROCURED

(a) APPLICABLE TO PART II - Parts

The parts below should be procured from Embraer as spare part.

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ALERT SB No.: 500-55-A004

PAGE: 4

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

Copyright © 2014 by Embraer S.A. All rights reserved.
NEW PN DESCRIPTION OLD PN QTY DISP

RMLH2577-070

BARREL SELFLOCKING NUT

NAS577B7A 04 3

NOTE: The old Part Number shall be with the chamfered edge.

(b) APPLICABLE TO PART II - Consumable Materials

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.

NOTE: When applicable, the use of alternative consumable material in place of

the ones specified is allowable, provided that these alternative are

approved by Embraer as indicated in the related Embraer Technical

Publications or through a formal Embraer communication channel.

NEW PN DESCRIPTION OLD PN QTY DISP

Cor-Ban 27L

Corrosion Inhibitor

Compound (Spec MEP

09- 075)

- AR 6

P/S870C-12

or

P/S870C-12 654 SEM

KIT

or

P/S870C-12 MC 780

C-12

Sealant (Spec MILPRF- 81733)

- AR 6

F-900-Red

or

F-925-Pink

or

F-925-Yellow

Torque Seal (Spec

MEP 09-068)

- AR 6

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ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 5

Copyright © 2014 by Embraer S.A. All rights reserved.
NEW PN DESCRIPTION OLD PN QTY DISP

Alodine 1200

or

Alodine 1200S

or

Bonderite M-CR

1200S AERO

Alodine (Spec MILDTL-81706)

- AR 6

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ALERT SB No.: 500-55-A004

PAGE: 6

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

Copyright © 2014 by Embraer S.A. All rights reserved.
3. ACCOMPLISHMENT INSTRUCTIONS

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.

B. Remove the front boom fairing according to instructions given in AMM TASK 55-32-23-

000-801-A/400 - Front Boom Fairing - Removal.

C. APPLICABLE TO PART I:

(1) Inspect the barrel self-locking nuts. If one or more barrel self-locking nuts is of the

same type shown in Figure 1 C2, NOT ACCEPTABLE replace it/them as given in

PART II. Otherwise go to Step 3.E.

(2) For removed nuts, fill up the table given in 4. APPENDIX 2 with the requested

information, send it and contact Embraer Technical Support Department through

contact.center@embraer.com.

D. APPLICABLE TO PART II

(1) Replace the barrel self-locking nut according to instructions given in Figure 2.

NOTE: Be careful not to damage the de-icer assembly tubes when you replace the

barrel self-locking nuts.

NOTE: Be careful not to drop into the vertical-stabilizer leading edge the barrel

self-locking nut when you remove it.

E. Reinstall the front boom fairing according to instructions given in AMM TASK 55-32-23-

400-801-A/400 - Front Boom Fairing - Installation.

F. Restore the aircraft to normal. Refer to AMM TASK 20-00-00-910-801-A/200 - Aircraft

Maintenance Safety Procedures.

G. Enter the accomplishment of this bulletin in the applicable documents.

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ALERT

ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 7

Copyright © 2014 by Embraer S.A. All rights reserved.
H. Fill out the attached “Service Bulletin Implementation and Evaluation” form and return it

to:

NOTE: 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).

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ALERT SB No.: 500-55-A004

PAGE: 8

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

Copyright © 2014 by Embraer S.A. All rights reserved.
EM500ENSB550015A.DGN

A

ZONES

335

343

344

A

B

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ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 9

FIGURE 1 - PART I - SELF-LOCKING NUTS INSPECTION

(SHEET 01 OF 03)

Copyright © 2014 by Embraer S.A. All rights reserved.
EM500ENSB550016A.DGN

B

C

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ALERT SB No.: 500-55-A004

PAGE: 10

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

FIGURE 1 - PART I - SELF-LOCKING NUTS INSPECTION

(SHEET 02 OF 03)

Copyright © 2014 by Embraer S.A. All rights reserved.
EM500ENSB550017A.DGN

C 1

C 2

FLAT EDGE

RETAINER

BARREL 

SELF−LOCKING NUT

CHAMFERED EDGE

RETAINER

BARREL 

SELF−LOCKING NUT

(NOT ACCEPTABLE NUT)

(ACCEPTABLE NUT)

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ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 11

FIGURE 1 - PART I - SELF-LOCKING NUTS INSPECTION

(SHEET 03 OF 03)

Copyright © 2014 by Embraer S.A. All rights reserved.
1. Replace the barrel self-locking nut as follows:

(a) Remove one bolt and its washer at a time following the installation sequence (1),

(2), (3) and (4) as shown in Det.B.

(b) Remove and discard the barrel self-locking nut PN NAS577B7A and retain its

retainer PN NAS578-7B.

WARNING : DURING THE CLEANING PROCEDURE, DO NOT LET THE

CLEANING SOLUTION TOUCH YOUR SKIN AND DO NOT

BREATHE ITS VAPORS OR MISTS. DO THE PROCEDURE IN AN

AREA WITH A GOOD AIRFLOW. PUT ON SAFETY CLOTHES,

GOGGLES, AND GLOVES.

(c) Clean the bolt and hole to remove the old sealant. Refer to SRM PART 2 51-22-01/1

- SURFACE FINISHING AND PROTECTION - CLEANING.

(d) Apply alodine to the hole according to instructions given in SRM PART 2 51-22-03/1

- SURFACE FINISHING AND PROTECTION - ALODINE APPLICATION.

(e) Apply corrosion inhibitor compound Cor-Ban 27L to the new barrel self-locking nut

PN RMLH2577-070.

(f) Install the retainer to the new barrel self-locking nut, and install it to the hole.

(g) Position the countersunk washer on the bolt observing its correct installation

position.

(h) Apply sealant to the bolt. Refer to SRM PART 2 51-21-05/1 - FASTENER

SEALING.

NOTE: Make sure that you do not apply sealant to the thread of the bolts.

NOTE: Do not remove the excess sealant extruded.

(i) Read the drag torque (torque necessary to overcome the braking resistance of the

barrel self-locking nut) on the torque wrench. The values are shown in table below:

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ALERT SB No.: 500-55-A004

PAGE: 12

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

FIGURE 2 - PART II - BARREL SELF-LOCKING NUTS REPLACEMENT

(SHEET 01 OF 04)

Copyright © 2014 by Embraer S.A. All rights reserved.
NOTE: If the drag torque value is out of the range, the barrel self-locking nut shall

be replaced.

Drag Torque

Bolt Position Bolt Diameter (in) Drag Torque (min.) Drag Torque (max.)

1, 2, 3 and 4 7/16 (1.6 N.m) 14 lb.in (11.2 N.m) 100 lb.in

(j) With a torque wrench, apply the pre-torque to the bolt.

Pre-Torque

Bolt Position Bolt Diameter (in) Pre-Torque

1, 2, 3 and 4 7/16 (19.2 N.m) 170 lb.in

(k) Wait 15 minutes, release the pre-torque and apply the final tightening torque to the

bolt.

(l) Add the measured drag torque value to the tightening torque ((73.4 N.m) 650 lb.in).

The final tightening torque value is shown in the table below:

NOTE: The torque wrench shall be adjusted to the specified nominal value ((73.4

N.m) 650 lb.in) plus the previously measured drag torque (drag torque

measured at step above 1.(i) Figure 2).

Final Tightening Torque

Bolt Position Bolt Diameter (in) Final Tightening Torque

1, 2, 3 and 4 7/16 (73.4 N.m) 650 lb.in + drag

torque

2. Apply inspection torque seal to the head of the bolt.

3. Replace the next barrel self-locking nut and repeat the steps 1 to 2, as applicable.

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ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 13

FIGURE 2 - PART II - BARREL SELF-LOCKING NUTS REPLACEMENT

(SHEET 02 OF 04)

Copyright © 2014 by Embraer S.A. All rights reserved.
EM500ENSB550013A.DGN

A

ZONES

335

343

344

A

B

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ALERT SB No.: 500-55-A004

PAGE: 14

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

FIGURE 2 - PART II - BARREL SELF-LOCKING NUTS REPLACEMENT

(SHEET 03 OF 04)

Copyright © 2014 by Embraer S.A. All rights reserved.
EM500ENSB550014B.DGN

01

02

B

02

03

SEALANT P/S 870C−12

COR−BAN 27L

04

COUINTERSUNK WASHER

PN MS21299−C7

(4 POSITIONS)

(REUSE)

1 2

1

BOLT (3)

PN NAS21134−07020

(REUSE)

BOLT (1)

PN NAS21134−07020

(REUSE)

BOLT (2)

PN NAS21134−07020

(REUSE) BOLT (4)

PN NAS21134−07020

(REUSE)

02 04 05

02 04 05

02 04 05

05

04

05

APPLY TORQUE ACCORDING TO STEP 1

ALODINE 1200

TORQUE SEAL

RETAINER

PN NAS578−7B

(4 POSITIONS)

(REUSE)

3

1

1

BARREL 

SELF−LOCKING NUT

PN NAS577B7A

(4 POSITIONS)

(REMOVE AND

DISCARD)

3

1

01

BARREL 

SELF−LOCKING NUT

PN RMLH2577−070

(4 POSITIONS)

(INSTALL)

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ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 15

FIGURE 2 - PART II - BARREL SELF-LOCKING NUTS REPLACEMENT

(SHEET 04 OF 04)

Copyright © 2014 by Embraer S.A. All rights reserved.
4. APPENDIX 1

BARREL SELF-LOCKING NUTS

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PAGE: 16

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

Copyright © 2014 by Embraer S.A. All rights reserved.
(NOT ACCEPTABLE NUT)

CHAMFERED 

EDGE

(ACCEPTABLE NUT)

FLAT EDGE

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ALERT DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

SB No.: 500-55-A004

PAGE: 17

Copyright © 2014 by Embraer S.A. All rights reserved.
4. APPENDIX 2

Removed Nuts (Position) Cracked or Broken

Nuts Flight Cycles Flight Hours Aircraft Serial Number

yes ( )

no ( )

yes ( )

no ( )

yes ( )

no ( )

yes ( )

no ( )

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PAGE: 18

DATE: 21/Jul/2014

REVISION No.: 02 - 25/Jul/2014

Copyright © 2014 by Embraer S.A. All rights reserved.