# Embraer Service Bulletin 505-32-0011

Copy: Revision 01 ("U.S. DOT/FAA - SB505-32-0011"), 43 pages: PDF https://openairdocs.org/files/sha256/06/72/0672270089849f387afeb32592f47fb4ae343f4fd39151d9e7dea98f615e57fe; text https://openairdocs.org/service-documents/embraer/sb-505-32-0011/file/067227008984.md. Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2014-0390; AD 2014-19-01 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: 505-32-0011
- Latest revision known: 505-32-0011, Revision 01, dated March 31, 2014 (OpenAirDocs)
- Page: https://openairdocs.org/service-documents/embraer/sb-505-32-0011

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

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

- [AD 2014-19-01](https://openairdocs.org/ad/2014-19-01.md), effective Oct 22, 2014: Revision 01

Also cited in [1 proposed AD](https://openairdocs.org/service-documents/embraer/sb-505-32-0011/proposed.md).

## Text (43 pages)

Rights: © Embraer S.A. Filed by the FAA in regulations.gov docket FAA-2014-0390; AD 2014-19-01 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 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.

### Page 2

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
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REVISION No.: 01 - 31/Mar/2014
SB No.: 505-32-0011
PAGE: 1 of 41
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### Page 3

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
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### Page 4

– 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 accom-
plished.
– 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 accom-
plished 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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REVISION No.: 01 - 31/Mar/2014
SB No.: 505-32-0011
PAGE: 3
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### Page 5

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.

### Page 6

– 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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REVISION No.: 01 - 31/Mar/2014
SB No.: 505-32-0011
PAGE: 5
Copyright © 2014 by EMBRAER S.A. All rights reserved.

### Page 7

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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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.

### Page 8

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. See2.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 man-
hours 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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REVISION No.: 01 - 31/Mar/2014
SB No.: 505-32-0011
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Copyright © 2014 by EMBRAER S.A. All rights reserved.

### Page 9

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 PARTI-T oa l l 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 3o r7
1. Installation as a set is not required.
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PAGE: 8
DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
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### Page 10

Applicable to PART I and/or PART II - For all aircraft under TCCA certifica-
tion
NEW PN [1] DESCRIPTION OLD PN QTY DISP
DAP00097-02 Brake Assembly DAP00097-02 AR 7
1. Installation as a set is not required.
DISPOSI-
TION:
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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SB No.: 505-32-0011
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### Page 11

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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### Page 12

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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### Page 13

(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 ACTU-
ATED. 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 instructions4.
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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REVISION No.: 01 - 31/Mar/2014
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### Page 14

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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### Page 15

(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 accom-
plished.
(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 toFigure 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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### Page 16

– 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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SB No.: 505-32-0011
PAGE: 15
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### Page 17

B
282O 1282OOO
BARO
ILS STD
+
−
CAGE
1013HPA
340
ILS1 M57577
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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DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
FIGURE1-P A R TI/I Ia n dI I I- EMERGENCY PARKING BRAKE ACTUATION
(SHEET 01 OF 01)
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### Page 18

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
FIGURE2-P A R TI- PRESSURE STATOR INSPECTION - GENERAL VISUAL INSPECTION
(SHEET 01 OF 01)
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### Page 19

LEGEND:
AREA TO BE INSPECTED.
EM500ENSB320061B.DGN
A
ZONES
721
731
BLOCKING ACTUATOR(REF.)
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
A
B
BRAKE ASSEMBLY
(REF.)
C
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PAGE: 18
DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
FIGURE3-P A R TI- PRESSURE STATOR INSPECTION - DETAILED VISUAL INSPECTION
(SHEET 01 OF 02)
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### Page 20

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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FIGURE3-P A R TI- PRESSURE STATOR INSPECTION - DETAILED VISUAL INSPECTION
(SHEET 02 OF 02)
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### Page 21

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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DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
FIGURE4-P A R TI I- DISC INSPECTION - DETAILED VISUAL INSPECTION
(SHEET 01 OF 05)
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### Page 22

EM500ENSB320071A.DGN
INSPECT THE ENTIRE DISK CIRCUMFERENCE01
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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FIGURE4-P A R TI I- DISC INSPECTION - DETAILED VISUAL INSPECTION
(SHEET 02 OF 05)
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### Page 23

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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FIGURE4-P A R TI I- DISC INSPECTION - DETAILED VISUAL INSPECTION
(SHEET 03 OF 05)
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### Page 24

D F
TYPICAL
E
H
H
H
EM500ENSB320073A.DGN
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FIGURE4-P A R TI I- DISC INSPECTION - DETAILED VISUAL INSPECTION
(SHEET 04 OF 05)
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### Page 25

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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DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
FIGURE4-P A R TI I- DISC INSPECTION - DETAILED VISUAL INSPECTION
(SHEET 05 OF 05)
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### Page 26

4. APPENDIX 1
TYPICAL CRACKS
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### Page 27


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### Page 28

4. APPENDIX 2
MEGGITT SB
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### Page 29

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1001 
Copyright Ó 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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### Page 30

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1002 
Copyright Ó 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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### Page 31

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1003 
Copyright Ó 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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### Page 32

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1004 
Copyright Ó 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 compo nent 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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### Page 33

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1005 
Copyright Ó 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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### Page 34

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1006 
Copyright Ó 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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### Page 35

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1007 
Copyright Ó 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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### Page 36

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1008 
Copyright Ó 2013 Meggitt Aircraft Braking Systems 
 
 
 
 
FIGURE 1 - Brake Assembly 
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### Page 37

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1009 
Copyright Ó 2013 Meggitt Aircraft Braking Systems 
 
 
 
 
 
 
FIGURE 2 - Heat Pack Assembly 
 
 
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### Page 38

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1010 
Copyright Ó 2013 Meggitt Aircraft Braking Systems 
 
 
FIGURE 3 - Cylinder Assembly 
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### Page 39

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1011 
Copyright Ó 2013 Meggitt Aircraft Braking Systems 
 
 
FIGURE 4 - HeatPack Wear Indicator 
 
 
 
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TM
ÀREA DE NÃO INTERFERÊNCIA
SERVICE BULLETIN
SB No.: 505-32-0011
PAGE: 38
DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
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### Page 40

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1012 
Copyright Ó 2013 Meggitt Aircraft Braking Systems 
 
 
 
FIGURE 5 - Wear Pin Crop Instruction 
 
 
 
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ÀREA DE NÃO INTERFERÊNCIA
SERVICE BULLETIN
DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
SB No.: 505-32-0011
PAGE: 39
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### Page 41

SERVICE BULLETIN 
 SB-32-1625 Rev A 
Oct 17/13 Page 1013 
Copyright Ó 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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ÀREA DE NÃO INTERFERÊNCIA
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PAGE: 40
DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
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### Page 42

4. APPENDIX 3
INSPECTION FORM
Side
Brake Assembly
Disc
Brake Cycles
since Installa-
tion
Crack Dimensions
PN SN Longitudinal Transversal
Aircraft Data
Serial Number Incorporation Date Flight Cycles Flight Hours
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SERVICE BULLETIN
DATE: 11/Feb/2014
REVISION No.: 01 - 31/Mar/2014
SB No.: 505-32-0011
PAGE: 41
Copyright © 2014 by EMBRAER S.A. All rights reserved.

### Page 43

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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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