## 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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 brakeassembly 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 loggedHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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 PAR T 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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, BrasilHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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 28 2 O 128 2O OO

BARO ILS STD

+

−

CAGE 1013HPA

340 ILS1 M 57577

320

280 260 57 M IRS1 32 34 10 26 000
5757

28 500 10 

## A



# A

B

BEM500ENSB320063A.DGN T−HANDLE T−HANDLE (ROTATED 90° CLOCKWISE) BRAKE INDICATING LAMPHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 16 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 FIGUR E 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.DGNHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 17 FIGUR E 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 

## B LOCKING ACTUATOR (REF.)

LEFT SIDE SHOWN RIGHT SIDE OPPOSITE 

# A

B BRAKE ASSEMBLY (REF.)



## CHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 18 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 FIGUR E 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.)

01EM500ENSB320062B.DGN STATOR PRESSURE PLATE 

## D 01

LEGEND: AREA TO BE INSPECTED.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 19 FIGUR E 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 

# AEM500ENSB320070A.DGNHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 20 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 FIGUR E 4 - PART II - DISC INSPECTION - DETAILED VISUAL INSPECTION (SHEET 01 OF 05)

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

INSPECT THE ENTIRE DISK CIRCUMFERENCE 01 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 SURFACESHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 21 FIGUR E 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 CRACKSEM500ENSB320072A.DGN



# GHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 22 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 FIGUR E 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

HEM500ENSB320073A.DGNHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 23 FIGUR E 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.) 

# HEM500ENSB000311A.DGNHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 24 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 FIGUR E 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 CRACKSHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 25 Copyright © 2014 by EMBRAER S.A. All rights reserved.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 26 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 Embraer Copyright © 2014. All rights reserved.

## 4. APPENDIX 2 MEGGITT SBHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 27 Copyright © 2014 by EMBRAER S.A. All rights reserved.

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE.

TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 28 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 Embraer Copyright © 2014. All rights reserved.

# 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 M A NUF ACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A CONSUM ABLE MA TERI AL. 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 29 Embraer Copyright © 2014. All rights reserved.

# 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 SAFE L Y LIFT THE BRAKE ASSEMBLY.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 30 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 Embraer Copyright © 2014. All rights reserved.

# 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 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 31 Embraer Copyright © 2014. All rights reserved.

# 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 M A NUF ACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A CONSUM ABLE MA TERI AL. (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 M A NUF ACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A CONSUM ABLE MA TERI AL. (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 M A NUF ACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A CONSUM ABLE MA TERI AL. (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).HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 32 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 Embraer Copyright © 2014. All rights reserved.

# 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 M A NUF ACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A CONSUM ABLE MA TERI AL. 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)HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 33 Embraer Copyright © 2014. All rights reserved.

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 34 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 Embraer Copyright © 2014. All rights reserved.

# SERVICE BULLETIN

SB-32-1625 Rev A Oct 17/13 Page 1008 Copyright  2013 Meggitt Aircraft Braking Systems FIGURE 1 - Brake AssemblyHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 35 Embraer Copyright © 2014. All rights reserved.

# SERVICE BULLETIN

SB-32-1625 Rev A Oct 17/13 Page 1009 Copyright  2013 Meggitt Aircraft Braking Systems FIGURE 2 - Heat Pack AssemblyHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 36 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 Embraer Copyright © 2014. All rights reserved.

# SERVICE BULLETIN

SB-32-1625 Rev A Oct 17/13 Page 1010 Copyright  2013 Meggitt Aircraft Braking Systems FIGURE 3 - Cylinder AssemblyHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 37 Embraer Copyright © 2014. All rights reserved.

# SERVICE BULLETIN

SB-32-1625 Rev A Oct 17/13 Page 1011 Copyright  2013 Meggitt Aircraft Braking Systems FIGURE 4 - HeatPack Wear IndicatorHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 38 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 Embraer Copyright © 2014. All rights reserved.

# SERVICE BULLETIN

SB-32-1625 Rev A Oct 17/13 Page 1012 Copyright  2013 Meggitt Aircraft Braking Systems FIGURE 5 - Wear Pin Crop InstructionHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 SB No.: 505-32-0011 PAGE: 39 Embraer Copyright © 2014. All rights reserved.

# 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 ToolsHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# SERVICE BULLETIN

SB No.: 505-32-0011 PAGE: 40 DATE: 11/Feb/2014 REVISION No.: 01 - 31/Mar/2014 Embraer Copyright © 2014. All rights reserved.

## 4. APPENDIX 3 INSPECTION FORM
Side Brake Assembly Disc Brake Cyclessince Installation Crack Dimensions PN SN Longitudinal Transversal

Aircraft Data Serial Number Incorporation Date Flight Cycles Flight HoursHARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. TM ÀREA DE NÃO INTERFERÊNCIA 

# 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.HARD COPY IS UNCONTROLLED. ONCE PRINTED, THIS PAGE MUST NOT BE RETAINED FOR REFERENCE. 

# 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:



### Embraer Copyright © 2014. All rights reserved.