1. DESCRIPTION

This sheet transmits Revision 01 to Service Bulletin 505-32-0011.

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 bulletin do not need any additional

action.

3. RECORD OF REVISION

Basic issue: 11/Feb/2014

Revision 01: 31/Mar/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.C. REASON / 02 Added reason for revision 01.

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TRANSMITTAL LETTER

SB No.: 505-32-0011

PAGE: 1 of 1

Copyright © 2014 by EMBRAER S.A. All rights reserved.
LANDING GEAR - PRECAUTIONARY INSPECTION IN THE CARBON DISCS OF THE

MLG BRAKE

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.

This service bulletin supersedes the SB505-32-A011.

1. PLANNING INFORMATION

A. SB EFFECTIVITY

Aircraft affected:

MODEL SN

EMB-505 ’Phenom 300’ 50500004 thru 50500144, 50500146 thru 50500155,

50500157 thru 50500162, 50500164, 50500165,

50500167 thru 50500170, 50500172 thru 50500184,

50500186, 50500190, 50500192, 50500193, 50500195,

50500196, and 50500198.

Affected component:

Brake Assemblies PN DAP00097-01 and PN DAP00097-02 installed on the aircraft.

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.

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SERVICE BULLETIN

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 1 of 41

Copyright © 2014 by EMBRAER S.A. All rights reserved.
In-production effectivity:

Not affected.

B. CONCURRENT REQUIREMENTS

None.

C. REASON

(1) HISTORY

Instances have been reported of cracks found in the carbon discs of the brake

assembly.

(2) OBJECTIVE

To perform a precautionary visual inspection for cracks in the carbon discs of the

brake assembly.

(3) EXPECTED BENEFITS

To make sure that there are no cracks beyond acceptable limits on all carbon discs

of the brake assembly.

(4) REVISION HISTORY

(a) Revision 01

– This revision is to inform that this bulletin supersedes the SB505-32-A011.

D. DESCRIPTION

This Service Bulletin is divided in 2 PARTS, as follows:

(1) APPLICABLE TO PART I

PART I presents precautionary visual inspection to be done on the pressure stator

of the LH and RH brake assemblies for cracks beyond acceptable limits.

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SERVICE BULLETIN

SB No.: 505-32-0011

PAGE: 2

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

Copyright © 2014 by EMBRAER S.A. All rights reserved.
– In case any cracks beyond acceptable limits are detected during this inspection,

the brake assembly must be repaired in accordance with Meggitt SB (4.

APPENDIX 2), and the visual inspection must be repeated according to 1.E.

COMPLIANCE, until the final action given in SB505-32-0013 is accomplished.

– In case no cracks beyond acceptable limits are detected, repeat this visual

inspection, according to 1.E. COMPLIANCE, until the final action given in

SB505-32-0013 is accomplished.

NOTE: For cracks beyond acceptable limits, the brake assembly must be repaired

or replaced within 3 Flight Cycle(s).

(2) APPLICABLE TO PART II

PART II presents precautionary visual inspection to be done on the thrust stator,

double stator and rotors of the LH and RH brake assemblies.

– In case no crack is detected or if a crack within the acceptable limit shown in

Figure 4 Det.G is found, repeat the precautionary visual inspection at each tire

change or at any maintenance action which requires the wheel removal,

whichever occurs first, until the final action given in SB505-32-0013 is accomplished.

– In case of crack within the specified limit shown in Figure 4 Det.H, the brake

assembly must be replaced within 40 Flight Cycle(s).

– In case of crack out of the specified limit (unacceptable cracks) shown in Figure

4 Det.H, the brake assembly must be replaced immediately with a brake

assembly of the same Part Number, or the SB505-32-0013 must be accomplished before the next flight.

E. COMPLIANCE

(1) APPLICABLE TO PART I

Embraer recommends that the inspection presented in this PART I be accomplished

as follows:

– For brake assemblies PN DAP00097-01 or DAP00097-02 which have logged

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SERVICE BULLETIN

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 3

Copyright © 2014 by EMBRAER S.A. All rights reserved.
from 0 (zero) thru 149 Flight Cycle(s) since installation (Time Since New or Time

Since Overhaul or Time Since Repair), no action is required until the brake

assembly reaches 150 Flight Cycle(s).

– For brake assemblies PN DAP00097-01 or DAP00097-02 which have logged

between 150 Flight Cycle(s) and 300 Flight Cycle(s) (TSN or TSO or TSR), the

first inspection must be accomplished within the next 30 Flight Cycle(s) and

repeated at the next tire change, or within 60 Flight Cycle(s) ± 3 Flight Cycle(s),

whichever occurs first.

– For brake assemblies PN DAP00097-01 or DAP00097-02 which have logged

more than 300 Flight Cycle(s) (TSN or TSO or TSR), the first inspection must be

accomplished within the next 10 Flight Cycle(s) and repeated at the next tire

change, or within 60 Flight Cycle(s) ± 3 Flight Cycle(s), whichever occurs first.

(2) APPLICABLE TO PART II

Embraer recommends that the visual inspection presented in this PART II be

accomplished in the next tire change and repeated at each tire change, or at any

maintenance action which requires the wheel removal, whichever occurs first.

F. APPROVAL

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

de Aviação Civil.

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 promptly available when

necessary.

This estimate does not include the sealant, paint, or adhesive curing time.

(1) APPLICABLE TO PART I

– Access opening: Not applicable.

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SERVICE BULLETIN

SB No.: 505-32-0011

PAGE: 4

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

Copyright © 2014 by EMBRAER S.A. All rights reserved.
– Modification: 2.0 man-hours.

– Access closure: Not applicable.

– Test: Not applicable.

NOTE: If a brake assembly replacement is necessary, an additional 3.0 man-hours

per side are required, and if necessary, add 1.5 man-hours for pressure

stator replacement.

(2) APPLICABLE TO PART II

– Access opening: Not applicable.

– Modification: 3.0 man-hours.

– Access closure: Not applicable.

– Test: Not applicable.

NOTE: If a brake assembly replacement is necessary, additional 3.0 man-hours per

side are required.

H. WEIGHT AND BALANCE

– Change in basic weight: None.

– Change in basic moment: None.

I. ELECTRICAL LOAD DATA

Not changed.

J. SOFTWARE ACCOMPLISHMENT SUMMARY

None.

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SERVICE BULLETIN

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 5

Copyright © 2014 by EMBRAER S.A. All rights reserved.
K. REFERENCES

AMM 505/( ) Aircraft Maintenance Manual PART II - 07-10-00 - LIFTING &

SHORING.

AMM 505/( ) Aircraft Maintenance Manual PART II - 20-00-00 - STANDARD

PRACTICES-AIRFRAME.

AMM 505/( ) Aircraft Maintenance Manual PART II - 24-41-00 - ELECTRICAL

POWER.

AMM 505/( ) Aircraft Maintenance Manual PART II - 29-10-00 - HYDRAULIC

POWER.

AMM 505/( ) Aircraft Maintenance Manual PART II - 32-40-00, 32-41-00, 32-45-

01, and 32-45-21 - LANDING GEAR.

L. PUBLICATIONS AFFECTED

AMM 505/( ) Aircraft Maintenance Manual PART II - 32-45-01 and 32-45-21 -

LANDING GEAR.

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SERVICE BULLETIN

SB No.: 505-32-0011

PAGE: 6

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

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

A. MATERIAL - PRICE AND AVAILABILITY

(1) MATERIAL AVAILABLE FROM EMBRAER

If necessary, the material required for the accomplishment of this bulletin will be

available from Embraer. See 2.C. MATERIAL NECESSARY FOR EACH AIRCRAFT.

B. INDUSTRY SUPPORT INFORMATION

(1) WARRANTY COVERAGE

(a) Parts

Parts will be provided at no charge on an exchange basis in case unacceptable

cracks are found.

(b) Labor

PART I: Embraer will compensate 2.0 man-hours for the SB incorporation if it is

performed in an Embraer-authorized service center.

NOTE: If a brake assembly replacement is necessary, an additional 3.0

man-hours per side are required, and if necessary, add 1.5 man-hours

for pressure stator replacement.

PART II: Embraer will compensate 3.0 man-hours for the SB incorporation if it

is performed in an Embraer-authorized service center.

NOTE: If a brake assembly replacement is necessary, additional 3.0 manhours per side are required.

(c) Expiration

The terms expressed in the warranty coverage will be valid for 24 months after

the SB issue date.

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SERVICE BULLETIN

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 7

Copyright © 2014 by EMBRAER S.A. All rights reserved.
C. MATERIAL NECESSARY FOR EACH AIRCRAFT

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

bulletin can be necessary for its accomplishment. Examine the operator’s inventories to

make sure all materials are available.

(1) MATERIAL TO BE PROCURED

(a) Parts

The parts below should be ordered as spares from Embraer, as a result of the

inspection:

– For Brake Repair:

Applicable to PART I - To all aircraft

NEW PN DESCRIPTION OLD PN QTY DISP

DAA05431-01 Stator, Pressure Assy DAA05431-01 AR 7

– For Brake Replacement:

Applicable to PART I and/or PART II - For all aircraft under ANAC, FAA

and EASA certification

NEW PN [1] DESCRIPTION OLD PN QTY DISP

DAP00097-01

or

DAP00097-02

Brake Assembly

DAP00097-01

or

DAP00097-02

AR 3 or 7

1. Installation as a set is not required.

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SERVICE BULLETIN

SB No.: 505-32-0011

PAGE: 8

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

Copyright © 2014 by EMBRAER S.A. All rights reserved.
Applicable to PART I and/or PART II - For all aircraft under TCCA certification

NEW PN [1] DESCRIPTION OLD PN QTY DISP

DAP00097-02 Brake Assembly DAP00097-02 AR 7

1. Installation as a set is not required.

DISPOSITION:7 = Replace with part bearing same PN

QUANTITY: AR = As Required

DISPOSITION: 3 = Replace part bearing OLD PN with part bearing NEW; 7=

Replace with part bearing same PN.

QUANTITY: AR = As Required

NOTE: Send the removed Brake Assemby to Embraer, at one of these

addresses:

Embraer (USA)

2250 Outer Loop Bldg#6 dock 701

Louisville, KY 40219 USA

Phone: +1 502 961 4541

Facsimile: +1 502 961 4878

Embraer (France)

Bât. Eddington Paris Nord 2

33 rue des Vanesses

BP 58294 Villepinte

95958 Roissy CDG Cedex

France

Phone: (+33 1) 49 38 4400

Facsimile: (+33 1) 49 38 4401

Embraer (Brazil)

Avenida Brigadeiro Faria Lima, 2170, Putim

CEP 12227-901 – São José dos Campos

São Paulo, Brasil

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SERVICE BULLETIN

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 9

Copyright © 2014 by EMBRAER S.A. All rights reserved.
Phone: (+55 12) 3927-1000

Facsimile: (+55 12) 3927 6600 Ext. 1448

D. MATERIAL NECESSARY FOR EACH SPARE

None.

E. REIDENTIFIED PARTS

None.

F. TOOLING - PRICE AND AVAILABILITY

None.

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SERVICE BULLETIN

SB No.: 505-32-0011

PAGE: 10

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/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. Energize the aircraft with an External DC Power Supply AMM TASK 24-41-00-860-801-

A/200 - Energization of the Aircraft with an External DC Power Supply - Aircraft/System

Configuration.

C. APPLICABLE TO PART I

(1) Clean the stator pressure to be inspected with a lint-free cloth moistened with

demineralized water. Refer to Figure 2.

(2) Pressurize the brake system, as follows:

(a) Look at the CAS and see if the message EMERG BRK LO PRESS is shown. If

this message is on, pressurize the hydraulic system with a hydraulic test stand

AMM TASK 29-10-00-910-802-A/200 - Main Hydraulic System - Hydraulic

System Pressurization with a Hydraulic Test Stand (HTS), or with the engines

AMM TASK 29-10-00-910-805-A/200 - Main Hydraulic System - Hydraulic

System Pressurization with Engines, if required.

(b) In the cockpit, apply the emergency/parking brake with the handle (brakes on).

Refer to Figure 1.

NOTE: Make sure that the emergency/parking brake is fully applied and

locked.

(c) Make sure that the ′′PARKING′′ lamp comes on and do a visual check to make

sure that all the pistons of the brake assembly are operated. Refer to Figure 1.

(3) Perform a general visual inspection for cracks in the pressure stator of LH and RH

brake assemblies. Refer to Figure 2.

NOTE: Only the pressure stator circumference must be inspected. See Figure 3.

NOTE: Use a flashlight and a mirror to do the inspection.

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SERVICE BULLETIN

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 11

Copyright © 2014 by EMBRAER S.A. All rights reserved.
(a) In case any crack is detected, do a detailed visual inspection with the wheel

removed. Go to Step 3.C.(4).

(b) In case no crack is detected, fill out the Inspection Form (4. APPENDIX 3) and

repeat this visual inspection periodically, according to 1.E. COMPLIANCE, until

the final action given in SB505-32-0013 is accomplished.

1 Release the emergency/parking brake. Go to Step 3.F.

(4) Release the emergency/parking brake and put a DO-NOT-OPERATE tag on the

handle.

(5) Using a jack, lift the wheel AMM TASK 07-10-00-580-803-A/200 - Partial Aircraft

Jacking.

WARNING : DO NOT GO NEAR THE AIRCRAFT TIRES WHEN THEY ARE HOT.

THE HIGH TEMPERATURE CAN CAUSE AN EXPLOSION OF THE

TIRES. IF IT IS NECESSARY TO GO NEAR THEM, GO FROM THE

FRONT IN RELATION TO THE FLIGHT DIRECTION. DO NOT GO

TO THE TIRES FROM THE SIDE.

(6) Remove the affected main wheel assembly from the aircraft according to AMM TASK

32-45-01-000-801-A/400 - Main Wheel Assembly - Removal. Refer to Figure 3.

WARNING : DO NOT TOUCH THE BRAKE ASSEMBLY WHILE IT IS ACTUATED. THIS IS TO PREVENT INJURIES TO PERSONNEL.

(7) Pull the T-handle to the end of its stroke and turn it 90 degrees clockwise.

(8) Perform a detailed visual inspection for cracks out of the acceptable limits in the

pressure stator of the brake assembly. Figure 3 shows the acceptable limits and

shows examples of cracks.

NOTE: Only the pressure stator circumference must be inspected.

NOTE: Use a flashlight and mirror to do the inspection.

(a) In case cracks out of the acceptable limits are detected during this inspection,

the brake assembly must be repaired in accordance with Meggitt instructions 4.

APPENDIX 2 and steps below, or replaced with a new one PN DAP00097-01 or

DAP00097-02. Repeat this visual inspection periodically, according to 1.E.

COMPLIANCE, until the final action given in SB505-32-0013 is accomplished.

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SB No.: 505-32-0011

PAGE: 12

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

Copyright © 2014 by EMBRAER S.A. All rights reserved.
NOTE: If any crack out of specified limits is detected, the brake assembly must

be repaired or replaced within 3 Flight Cycle(s).

NOTE: Fill out the Inspection Form (4. APPENDIX 3) and send it to your local

EMBRAER representatives or offices by email

phenom.reliability@embraer.com.br.

NOTE: Make sure that you include the current brake cycles since installation

(TSN or TSO or TSR) in the form and removal tag.

1 Release the emergency/parking brake and put a DO-NOT-OPERATE tag on

the handle.

2 Release the pressure from the hydraulic system according to AMM TASK

29-10-00-910-801-A/200 - Main Hydraulic System - Depressurization.

3 Remove the brake assembly according to AMM TASK 32-45-21-000-801-

A/400 - Brake Assembly - Removal.

4 Install a repaired or new brake assembly according to AMM TASK 32-45-

21-400-801-A/400 - Brake Assembly - Installation.

NOTE: Installation as a set is not required.

5 Install the main wheel assembly to the aircraft according to AMM TASK

32-45-01-400-801-A/400 - Main Wheel Assembly - Installation.

6 Lower and remove the jack from the wheel in accordance with AMM TASK

07-10-00-580-804-A/200 - Partial Aircraft Lowering.

7 Remove the DO-NOT-OPERATE flag from the emergency/parking brake

handle.

8 Do the procedure to bleed the air from the normal brake and

emergency/parking brake systems in accordance with AMM TASK 32-40-

00-870-801-A/200 - Normal Brake and Emergency/Parking-Brake Systems

- Bleeding.

9 Do the functional check of the main brake system according to AMM TASK

32-41-00-720-801-A/500 - Main Brake System - Functional Test.

10 Go to Step 3.E.

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REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 13

Copyright © 2014 by EMBRAER S.A. All rights reserved.
(b) In case no cracks out of the acceptable limits are detected, fill out the Inspection

Form (4. APPENDIX 3) and repeat this visual inspection periodically, according

to 1.E. COMPLIANCE, until the final action given in SB505-32-0013 is accomplished.

(9) Release the pressure from the hydraulic system according to AMM TASK 29-10-00-

910-801-A/200 - Main Hydraulic System - Depressurization.

(10) Install the main wheel assembly to the aircraft according to AMM TASK 32-45-01-

400-801-A/400 - Main Wheel Assembly - Installation.

(11) Lower and remove the jack from the wheel in accordance with AMM TASK

07-10-00-580-804-A/200 - Partial Aircraft Lowering.

(12) Remove the DO-NOT-OPERATE flag from the emergency/parking brake handle.

D. APPLICABLE TO PART II

(1) Remove the main wheel assembly according to AMM TASK 32-45-01-000-801-

A/400 - Main Wheel Assembly - Removal.

(2) Clean the thrust stator, double stator and rotors to be inspected with a lint-free cloth

moistened with demineralized water.

(3) Perform a general visual inspection for cracks on the external visible surface

(contour) of the thrust stator, double stator and rotors, as follow. Refer to Figure 4 for

the area to be inspected and the acceptable limits. Also, fill out the Inspection Form

(4. APPENDIX 3) and send it by e-mail to phenom.reliability@embraer.com.br.

(a) In case no crack is detected or if there are cracks within the acceptable limit

shown in Figure 4 Det.G, proceed as follows:

– Repeat the precautionary visual inspection at each tire change or at any

maintenance action which requires the wheel removal, whichever occurs first

until the final action given in SB505-32-0013 is accomplished.

(b) In case of crack within the specified limits shown in Figure 4 Det.H, proceed as

follows.

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SB No.: 505-32-0011

PAGE: 14

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

Copyright © 2014 by EMBRAER S.A. All rights reserved.
– The brake assembly must be replaced within 40 Flight Cycle(s).

(c) In case of cracks out of the specified limit (unacceptable cracks) shown in

Figure 4 Det.H, proceed as follows:

– The brake assembly must be replaced immediately with a brake assembly of

the same Part Number according to AMM MPP 32-45-21/400 - BRAKE

ASSEMBLY - REMOVAL/INSTALLATION or the SB505-32-0013 must be

accomplished before the next flight.

E. De-energize the aircraft according to AMM TASK 24-41-00-860-802-A/200 - Aircraft

De-energization - Aircraft/System Configuration.

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 PART I or PART II or PART III of this bulletin in the applicable

documents.

H. Fill out the "Service Bulletin Implementation and Evaluation" form and click on "Submit by

Email" button. To find the form, log in to the FlyEmbraer portal

(http://www.flyembraer.com) and go to: "Technical Publication > Technical Data > Service

Bulletin > Front Matter > SB505 - SERVICE BULLETIN IMPLEMENTATION AND

EVALUATION FORM".

You can also fill out the attached form and send it by mail or e-mail to the addresses given

in this form.

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SERVICE BULLETIN

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 15

Copyright © 2014 by EMBRAER S.A. All rights reserved.
B

282

O 1282O

OO

BARO

ILS STD

+

−

CAGE

1013HPA

340

ILS1 57577M

320

280

260

57M IRS1 32 34

10 26000

5757

28500

10

A

A

B

B

EM500ENSB320063A.DGN

T−HANDLE

T−HANDLE

(ROTATED 90°

CLOCKWISE)

BRAKE

INDICATING

LAMP

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SB No.: 505-32-0011

PAGE: 16

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

FIGURE 1 - PART I / II and III - EMERGENCY PARKING BRAKE ACTUATION

(SHEET 01 OF 01)

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

ZONES

721

731

01

A

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

B

PERFORM A VISUAL INSPECTION FOR CRACKS ALONG PRESSURE STATOR CIRCUMFERENCE

B

BRAKE ASSEMBLY

(REF.)

01

TIRE

STATOR

PRESSURE

PLATE

LEGEND:

AREA TO BE INSPECTED.

EM500ENSB320064B.DGN

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REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 17

FIGURE 2 - PART I - PRESSURE STATOR INSPECTION - GENERAL VISUAL INSPECTION

(SHEET 01 OF 01)

Copyright © 2014 by EMBRAER S.A. All rights reserved.
LEGEND:

AREA TO BE INSPECTED.

EM500ENSB320061B.DGN

A

ZONES

721

731

LOCKING ACTUATOR

(REF.) B

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

A

B

BRAKE ASSEMBLY

(REF.)

C

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SB No.: 505-32-0011

PAGE: 18

DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

FIGURE 3 - PART I - PRESSURE STATOR INSPECTION - DETAILED VISUAL INSPECTION

(SHEET 01 OF 02)

Copyright © 2014 by EMBRAER S.A. All rights reserved.
C

UNACCEPTABLE CRACKS

UNACCEPTABLE CRACKS

ACCEPTABLE CRACKS

D

E

E

INSPECT THE ENTIRE DISK CIRCUMFERENCE

3.3 mm (0.13 in.)

3.3 mm (0.13 in.)

3.3 mm (0.13 in.)

25.4 mm (1.00 in.)

25.4 mm (1.00 in.)

25.4 mm (1.00 in.)

25.4 mm (1.00 in.)

3.3 mm (0.13 in.)

01

EM500ENSB320062B.DGN

STATOR PRESSURE PLATE

D

01

LEGEND:

AREA TO BE INSPECTED.

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REVISION No.: 01 - 31/Mar/2014

SB No.: 505-32-0011

PAGE: 19

FIGURE 3 - PART I - PRESSURE STATOR INSPECTION - DETAILED VISUAL INSPECTION

(SHEET 02 OF 02)

Copyright © 2014 by EMBRAER S.A. All rights reserved.
B

BRAKE ASSEMBLY

(REF.)

C

A

ZONES

721

731

B

LOCKING ACTUATOR

(REF.)

LEFT SIDE SHOWN

RIGHT SIDE OPPOSITE

A

EM500ENSB320070A.DGN

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PAGE: 20

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REVISION No.: 01 - 31/Mar/2014

FIGURE 4 - PART II - DISC INSPECTION - DETAILED VISUAL INSPECTION

(SHEET 01 OF 05)

Copyright © 2014 by EMBRAER S.A. All rights reserved.
EM500ENSB320071A.DGN

01 INSPECT THE ENTIRE DISK CIRCUMFERENCE

02

DOUBLE STATOR

ROTOR

ROTOR

THRUST STATOR

LEGEND:

AREA TO BE INSPECTED.

C

D

E

F

E

01

02

01

02

INSPECT ALL THE ROTOR PROTRUSION AND RECESS SURFACES

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PAGE: 21

FIGURE 4 - PART II - DISC INSPECTION - DETAILED VISUAL INSPECTION

(SHEET 02 OF 05)

Copyright © 2014 by EMBRAER S.A. All rights reserved.
D F

TYPICAL

E

G

G

G

ACCEPTABLE CRACKS

5 mm (0.2 in.)

5 mm (0.2 in.)

5 mm (0.2 in.)

5 mm (0.2 in.)

UNACCEPTABLE CRACKS

5 mm (0.2 in.)

5 mm (0.2 in.)

UNACCEPTABLE CRACKS

EM500ENSB320072A.DGN

G

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REVISION No.: 01 - 31/Mar/2014

FIGURE 4 - PART II - DISC INSPECTION - DETAILED VISUAL INSPECTION

(SHEET 03 OF 05)

Copyright © 2014 by EMBRAER S.A. All rights reserved.
D F

TYPICAL

E

H

H

H

EM500ENSB320073A.DGN

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PAGE: 23

FIGURE 4 - PART II - DISC INSPECTION - DETAILED VISUAL INSPECTION

(SHEET 04 OF 05)

Copyright © 2014 by EMBRAER S.A. All rights reserved.
UNACCEPTABLE CRACKS

5 mm (0.2 in.)

5 mm (0.2 in.)

ACCEPTABLE CRACKS 

25.4 mm (1 in.)

25.4 mm (1 in.)

UNACCEPTABLE CRACKS

5 mm (0.2 in.)

25.4 mm (1 in.)

H

EM500ENSB000311A.DGN

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FIGURE 4 - PART II - DISC INSPECTION - DETAILED VISUAL INSPECTION

(SHEET 05 OF 05)

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

TYPICAL CRACKS

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4. APPENDIX 2

MEGGITT SB

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PAGE: 27

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1001 

Copyright  2013 Meggitt Aircraft Braking Systems

1. PLANNING INFORMATION 

A. EFFECTIVITY 

(1) Aircraft Affected 

(a) Phenom 300 

(2) Part Number 

(a) DAP00097-01 

(b) DAP00097-02 

B. REASON 

(1) Instances have been reported that cracks were found in the pressure plate of the brake 

assembly. 

C. DESCRIPTION 

(1) This service bulletin tells the operator how to replace the pressure stator assembly. 

D. COMPLIANCE 

(1) Meggitt Aircraft Braking Systems recommends compliance with this service instruction 

when the pressure stator has been removed, due to cracks being found and the heat pack 

is less than 85% worn. 

E. APPROVAL 

(1) The technical content of this service bulletin is approved under the authority of: Meggitt 

Aircraft Braking Systems ADOA AP156. 

F. MANPOWER 

(1) One and one half (1.5) Man-hours for replacement of the Pressure-Stator as described 

below.

G. WEIGHT AND BALANCE 

(1) Not changed. 

H. ELECTRICAL LOAD DATA 

(1) Not changed. 

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DATE: 11/Feb/2014

REVISION No.: 01 - 31/Mar/2014

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1002 

Copyright  2013 Meggitt Aircraft Braking Systems

I. REFERENCES 

(1) AP-2195 CMM 32-45-97. 

J. SOFTWARE ACCOMPLISHMENT SUMMARY 

(1) None. 

K. PUBLICATIONS AFFECTED 

(1) None. 

2. MATERIAL INFORMATION 

L. MATERIAL - PRICE AND AVAILABILITY 

(1) None. 

M. TOOLING - PRICE AND AVAILABILITY 

(1) N/A. 

3. ACCOMPLISHMENT INSTRUCTIONS 

A. TEST THE BRAKE ASSEMBLY 

Note: An equivalent procedure of paragraph 3.A.(1) may be completed on the aircraft before 

removing the brake from the axle, see paragraph 3.A.(2). 

(1) Test the brake assembly removed from aircraft. 

(a) Do the test procedures in clean conditions. Make sure that there is no contamination of 

the hydraulic test system and the brake unit. Clean a used brake unit before you do the 

test procedure. If necessary, use a vacuum cleaner and a soft bristle brush and 

remove carbon dust from the brake unit. 

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE MANUFACTURER AND YOUR 

LOCAL INSTRUCTIONS WHEN YOU USE A CONSUMABLE MATERIAL. 

CAUTION: DO NOT GET HYDRAULIC FLUID ON THE HEAT PACK. CONTAMINATION CAN MAKE IT 

UNSERVICEABLE. 

 

WARNING: OBEY SAFETY PRECAUTIONS APPLICABLE TO HIGH PRESSURE HYDRAULIC SYSTEMS. 

HYDRAULIC PRESSURES OF UP TO 310,5 BAR (4500 PSI) ARE USED FOR THE BRAKE UNIT TESTS. 

(b) Put the brake unit with the torque plate assembly (1-230) at the top. 

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1003 

Copyright  2013 Meggitt Aircraft Braking Systems

(c) Make sure that the heat pack (1-40) has protection against contamination with hydraulic fluid and 

the inlet connection of the brake unit is clean. 

(d) Connect the hydraulic supply (through a shut off valve) to the inlet connection of the brake unit 

and monitor with a Pressure Gage. The inlet which is not in use is to be open to atmosphere. 

(e) Bleed the Test Equipment and Brake Unit. 

i. Install a bleed tube on the bleed screw (1-140) farthest from the inlet. 

ii. Put the end of the bleed tube into hydraulic fluid in an empty container. 

iii. Apply a fluid pressure of 10.34 bar (150 psi) to the brake unit to cause the pistons (3-160) to 

move to push against the pressure stator assembly (2-10). 

iv. Open the bleed screw and monitor the hydraulic fluid that flows from the bleed screw (1-140) 

and look for bubbles in the hydraulic fluid. 

v. Close the shut off valve. 

vi. Open the bleed screw (1-140) and reduce the fluid pressure to 3,50 bar (50.8 psi) on the 

Brake Pressure Gage. 

vii. Examine the position of the pistons (3-160), they should have all retracted. 

viii. Close the bleed screw (1-140) and reduce the fluid pressure to zero. 

ix. Repeat as many times as necessary to remove all trapped air from the brake. 

(f) High pressure leakage test: 

i. Apply a fluid pressure of 207 bar (3000 psi) to the brake unit. 

ii. Hold pressure on the brake unit for 5 minutes. 

iii. Examine the brake unit for leakage. No leakage is permitted. 

iv. Reduce the fluid pressure to zero. 

(2) Alternatively to the procedure described in paragraph 3.A.(1) above, follow the main brake 

system – functional test, in accordance with the Aircraft Maintenance Manual (reference: 

AMM TASK PART II 32-41-00-720-801-A). 

(3) Measure and record wear indicator remaining length: 

(a) Apply a fluid pressure of 193 bar +/-13 (2600 - 3000 psi) to the brake unit. 

(b) On each wear indicator measure and record the remaining life. See Figure 4. 

Note: Exposed portions of pistons may be cleaned while they are extended 

(4) Do the end test procedure: 

 

(a) Make sure that the fluid pressure has been released, and the stop valve is closed (Hydraulic 

supply). 

(b) Remove the brake unit from the test equipment or follow the Aircraft Maintenance Manual - 

Brake Assembly Removal (reference: AMM TASK PART II 32-45-21-000-801-A/400). 

B. DISASSEMBLE BRAKE ASSEMBLY: 

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE MANUFACTURER AND YOUR 

LOCAL INSTRUCTIONS WHEN YOU USE A CONSUMABLE MATERIAL. 

WARNING: THE BRAKE ASSEMBLY IS HEAVY. USE THE APPLICABLE EQUIPMENT TO SAFELY LIFT 

THE BRAKE ASSEMBLY. 

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REVISION No.: 01 - 31/Mar/2014

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1004 

Copyright  2013 Meggitt Aircraft Braking Systems

CAUTION: DO NOT ATTACH BRAKE LIFTING FIXTURES TO THE TORQUE TUBE PEDESTAL. THE 

BRAKE WEIGHT CAN CAUSE THE PEDESTAL TO BEND 

(1) Removal of Torque Plate Assembly from Torque Tube Assembly 

(a) Use an applicable lifting tool to put the brake unit on a clean bench with the torque plate 

assembly (1-230) at the top. 

(b) Remove the nuts (1-10), washers (1-20) and bolts (1-30) that attach the torque tube assembly (1-

50) to the torque plate assembly. After removal, clean nuts, bolts and washers prior to 

reassembly. 

(c) Remove the torque plate assembly (1-230) from the torque tube assembly (1-50). Clean these 

components sufficiently to allow proper re-assembly. Remove old jointing compound from 

mating surfaces. 

(2) Removal of Heat Pack Component – Pressure Stator Assembly 

(a) Remove the Pressure Stator (2-10) heat pack component from the torque tube assembly (1-

50), and identify as you remove it: 

• The pressure stator assembly (2-10) (identify with Brake Serial number) 

NOTE: Use marking tape or an alternative applicable procedure, to identify the pressure stator assembly (2-

10). An applicable procedure is one that causes no damage to a rotor or stator. 

NOTE: Identify the heat pack assembly and any removed or disassembled components so that the brake 

unit from which it was removed may be correlated at a later date. 

(b) Alternative pin setting (pre-cutting). 

i. Make dimension A the same for the new (replacement) pressure stator assembly as 

it is for the old (removed) pressure stator assembly as shown in Figure 5. 

Dimension A is from top of wear indicator to underside (working face) of the 

pressure stator disc. Mark and cut the wear indicator pin of the new pressure stator 

to dimension A. Remove any metal particles from the pressure stator assembly. 

(c) Return the removed Pressure Stator to Meggitt Aircraft Braking Systems at the closest 

of the following locations to the attention of (Customer Support – Phenom 300): 

• 1204 Massillon Rd., Akron, OH 44306, USA 

• Holbrooke Lane, Coventry, England CV6 4AA, UK 

C. ASSEMBLE THE BRAKE ASSEMBLY: 

(1) Use suitable protection to prevent damage occurring on the torque plate assembly and 

piston assemblies, press back all piston assemblies into the torque plate assembly: 

(a) Release bleed screws and capture surplus hydraulic fluid in a suitable container. 

(b) Fully press back each piston assembly. 

(c) Close the bleed screws. 

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1005 

Copyright  2013 Meggitt Aircraft Braking Systems

(2) Put the replacement pressure stator assembly (2-10) on the torque tube assembly (1-50); 

make sure the alignment groove of the pressure stator is in line with the alignment 

grooves of the rest of the heat pack. 

(3) Installation of Cylinder Assembly (1-220) and Heat Pack Assembly (1-40) with Torque 

Plate Assembly (1-230). 

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE MANUFACTURER AND YOUR 

LOCAL INSTRUCTIONS WHEN YOU USE A CONSUMABLE MATERIAL. 

(a) Apply a thin layer of jointing compound CA1000 to: 

• The shank of each bolt (1-30). 

• Below the head of each bolt (1-30). 

• Mating surfaces of the torque tube assembly (1-50) and the torque plate 

assembly (1-230). 

(b) Install the torque plate assembly (1-230) with cylinder assembly (1-220) on the torque 

tube assembly (1-100) with heat pack assembly (1-40). Make sure that the wear 

indicators engage with their related holes in the torque plate assembly (1-230). 

(c) Install the bolts (1-30) into the torque tube assembly (1-50). 

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE MANUFACTURER AND YOUR 

LOCAL INSTRUCTIONS WHEN YOU USE A CONSUMABLE MATERIAL. 

(d) Apply a thin layer of jointing compound CA1000 on one side of each washer (1-20). 

(e) Install a washer (1-20) on each bolt (1-30). Make sure that: 

• The jointing compound is kept off the threads of the bolts (1-30). 

• The surface with the jointing compound on is against the torque plate assembly (1-230) and 

cylinder assembly (1-220). 

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE MANUFACTURER AND YOUR 

LOCAL INSTRUCTIONS WHEN YOU USE A CONSUMABLE MATERIAL. 

(f) Apply a thin layer of anti-seize grease (SAE AMS2518 (ZX13, DEF STAN 80-80/1) to: 

• The threads of each bolt (1-30) 

• The bottom surface of each nut (1-10). 

(g) Install a nut (1-10) on each bolt (1-30) with washer (1-20). 

i. Torque each nut (1-10) to 53,0 Nm (39.0 lbf ft). 

D. TEST THE BRAKE ASSEMBLY: 

Note: An equivalent procedure may be completed after installing the brake on the aircraft. See 

paragraph 3.D.(1).(e). 

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REVISION No.: 01 - 31/Mar/2014

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1006 

Copyright  2013 Meggitt Aircraft Braking Systems

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE MANUFACTURER AND YOUR 

LOCAL INSTRUCTIONS WHEN YOU USE A CONSUMABLE MATERIAL. 

CAUTION: DO NOT GET HYDRAULIC FLUID ON THE HEAT PACK. CONTAMINATION CAN MAKE IT 

UNSERVICEABLE. 

WARNING: OBEY SAFETY PRECAUTIONS APPLICABLE TO HIGH PRESSURE HYDRAULIC SYSTEMS. 

HYDRAULIC PRESSURES OF UP TO 310,5 BAR (4500 PSI) ARE USED FOR THE BRAKE UNIT TESTS. 

(1) Test the brake assembly to be installed on the aircraft. 

(a) Connect and bleed the brake as instructed above in 3. A. (1) (a) through (e). When 

bleeding is complete, torque bleeder screw to 3.5 Nm (31.0 lbf in) 

(b) Brake Operational Test 

i. Apply a fluid pressure of 207 bar (3000 psi) to the brake unit. 

ii. Make sure all brake pistons move to their brake applied positions, to clamp the heat pack. 

iii. Decrease the brake pressure to 3,50 bar (50.8 psi). 

iv. Make sure that all the brake pistons retract to their initial position. Check that the gap 

between the each piston cap assembly (3-20) and the pressure stator assembly (2-10) is at 

least 0.015 inches. 

v. Decrease the brake pressure to zero. 

vi. Gradually apply a fluid pressure of 10,34 bar (150 psi). 

vii. Make sure that the brake heatpack is tightly held. 

viii. Decrease the fluid pressure to zero. 

(c) High pressure leakage test: 

i. Apply a fluid pressure of 207 bar (3000 psi) to the brake unit. 

ii. Hold pressure on the brake unit for 5 minutes. 

iii. Examine the brake unit for leakage. No leakage is permitted. 

iv. Reduce the fluid pressure to zero. 

(d) Low pressure leakage test: 

i. Apply a fluid pressure of 0,345 bar (5 psi) to the brake unit. 

ii. Hold the pressure on the brake unit for 5 minutes. 

iii. Examine the brake unit for leakage. No leakage is permitted. 

iv. Decrease the fluid pressure to zero. 

(2) Alternatively to the procedure described in steps 3.D.(1).(a) through (d) above, the brake 

assembly test may be performed with the brake unit installed on the aircraft, following the 

Aircraft Maintenance Manual - Main Brake System Functional Test (reference: AMM TASK 

PART II 32-41-00-720-801-A). 

(3) Crop the wear indicator to length recorded: (perform this sequence if 3.B.(2) (b) was not 

accomplished.) If 3.B.(2) (b) was accomplished, skip (a) and (b) below. 

Note: If the wear indicator pin was pre-cut in accordance with step 3.B.(2) (b) , only verification of 

the wear indicator pin length is required in step (c) below. If the pre-cut wear indicator length is too 

long, use a file or equivalent to bring it into compliance with the smallest measurement recorded in 

step 3.A.(3)(b). 

(a) Apply a fluid pressure of 193 bar +/-13 (2600 - 3000 psi) to the brake unit. 

(b) Crop the wear indicator to the lowest of the two wear indicator measurements that was recorded 

earlier in step 3.A.(3) (b). (See Figure 4) 

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1007 

Copyright  2013 Meggitt Aircraft Braking Systems

(c) Measure and record the wear indicator length for each wear indicator pin. 

(4) Do the end of test procedures (perform this sequence if 3.D.(1)(a) through (d) was 

accomplished): 

(a) Make sure that the fluid pressure has been released, and the stop valve is closed (Hydraulic 

stand) 

(b) Remove the brake unit from the test equipment. 

(5) Records 

(a) Record in your maintenance records that this service bulletin has been satisfied. 

Include the pressure stator assembly removed serial number, wear indicator recorded 

length and replacement pressure stator assembly serial number. 

4. MORE DATA 

(1) If you have a question related to this service bulletin, please contact your Meggitt Aircraft 

Braking Systems Local Area Manager. 

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1008 

Copyright  2013 Meggitt Aircraft Braking Systems

FIGURE 1 - Brake Assembly 

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1009 

Copyright  2013 Meggitt Aircraft Braking Systems

FIGURE 2 - Heat Pack Assembly 

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1010 

Copyright  2013 Meggitt Aircraft Braking Systems

FIGURE 3 - Cylinder Assembly 

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1011 

Copyright  2013 Meggitt Aircraft Braking Systems

FIGURE 4 - HeatPack Wear Indicator 

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1012 

Copyright  2013 Meggitt Aircraft Braking Systems

FIGURE 5 - Wear Pin Crop Instruction

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SERVICE BULLETIN 

SB-32-1625 Rev A 

Oct 17/13 Page 1013 

Copyright  2013 Meggitt Aircraft Braking Systems

The Figure 6 shows optional equivalent tools that may be used for this maintenance activity 

FIGURE 6 - Optional Equivalent Tools 

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REVISION No.: 01 - 31/Mar/2014

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4. APPENDIX 3

INSPECTION FORM

Side Brake Assembly Disc

Brake Cycles

since Installation

Crack Dimensions

PN SN Longitudinal Transversal

Aircraft Data

Serial Number Incorporation Date Flight Cycles Flight Hours

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PAGE: 41

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SERVICE BULLETIN IMPLEMENTATION

AND EVALUATION FORM

The purpose of this form is to collect data that will be used to improve the quality of our Service Bulletins and Reliability

Program.

EMBRAER S.A.

Phenom Maintenance Support

Av. Brig. Faria Lima, 2170

São José dos Campos - SP

CEP: 12227-901 - PO Box: 36/2

BRASIL

Fax: ++ 55 12 3927-2619

e-mail: phenom.reliability@embraer.com.br

SB Number/Revision: SB Title:

SB Implementation Report

Aircraft Serial Number or Registration Number: Incorporation Date:

Aircraft Flight Hours: Aircraft Landings:

SB Evaluation (Check applicable boxes below and use the space as required to provide any additional information)

Estimated Manpower: [ ] OK [ ] NOT OK

Material & Kits: [ ] OK [ ] NOT OK

Accomplishment Instructions: [ ] OK [ ] NOT OK

Figures: [ ] OK [ ] NOT OK

SB General Evaluation: [ ] OK [ ] NOT OK

Comments:(Bulletin quality, difficulties found at the time of incorporation, suggested improvements, other)

Company/ Service Center: E-mail: Phone:

Address:

Form filled by: Work Order:

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