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Temporary Revision No. 32-4: Part Number 2-1684

MLG BRAKE PN 2-1684

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100% found this document useful (2 votes)

1K views188 pages

Temporary Revision No. 32-4: Part Number 2-1684

MLG BRAKE PN 2-1684

Uploaded by

enadnan

We take content rights seriously. If you suspect this is your content, claim it here.

Available Formats

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You are on page 1/ 188

GOODRICH CORPORATION, A PART OF COLLINS AEROSPACE

COMPONENT MAINTENANCE MANUAL

Part Number 2-1684

TEMPORARY REVISION NO. 32-4

The location of the Temporary Revision page is opposite the affected page in this CMM.

Page Affected: 6004

U.S. Export Classification: EAR 9E991 32-41-87

COLLINS AEROSPACE PROPRIETARY Page 1 of 2
Subject to the restriction on the cover page. Feb 22/22
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
Part Number 2-1684

TEMPORARY REVISION NO. 32-3

The location of the Temporary Revision pages are opposite the affected pages in this CMM.

Pages Affected: 9001, 9002, 9007

UTC AEROSPACE SYSTEMS PROPRIETARY

32-41-87 Page 1 of 4
Oct 28/20
U.S. Export Classification: EAR 9E991
**Printed copies are considered UNCONTROLLED – Verify current issue before use**
AIRCRAFT WHEELS AND BRAKES
GOODRICH CORPORATION
101 WACO STREET
P.O. BOX 340
TROY, OHIO 45373
U.S.A.
TEL: 937-339-3811
FAX: 937-440-2055
https://techpubs.goodrich.com

CAGE: 97153

TRANSMITTAL SHEET

TO: HOLDERS OF COMPONENT MAINTENANCE MANUAL 32-41-87, Revision No. 1 dated Jun 30/10 is
attached.

FILING INSTRUCTIONS

File the TRANSMITTAL SHEET separately.

This Revision No. 1 replaces Revision No. 0 of this manual dated Dec 20/04.

TRANSMITTAL
Page 1
Jun 30/10
This document is subject to the controls and restrictions on the first page.
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

HIGHLIGHTS
Revision No. 1 - Jun 30/10

PAGES DESCRIPTION OF CHANGE

All Added an EAR statement to the Title page and a reference to this statement on
all other pages.

All Added change bars only to show important changes to data.

All Revised and added CAUTIONS and WARNINGS for procedures as applicable.

Introduction Revised data of specification sources.

Testing and Fault

Isolation Revised pressure values for the high pressure leak test and functional tests.

Testing and Fault

Isolation Revised illustration 1001.

Cleaning,
Special Tools,
Fixtures, Equipment,
and Consumables Added sodium bicarbonate as a paint removal abrasive.

Inspection/Check Revised the job set-up information for the Inspection/Check section.

Inspection/Check Added a procedure to check for loose rotor clips.

Inspection/Check Added a procedure for inspection of catalytic oxidation on carbon parts.

Inspection/Check Revised dimensions for Figure 5005.

Inspection/Check Removed the need for eddy current and penetrant inspections on the mounting
flange on the piston housing.

Inspection/Check Revised the procedure for the temperature sensor inspection.

Inspection/Check Added a visual inspection procedure of the bolts and the inspection options to
these bolts.

Inspection/Check Revised the procedure for the hardness inspection of the piston housing.

Repair Revised dimensions for Figure 6002.

Repair Introduced a plug repair for the bleeder port.

Assembly Added UniFlor® as a lubricant to be used in the assembly procedure of the

brake.

Assembly Added UniFlor® as a lubricant to be used in the assembly procedure of the

brake.

Assembly Added a step to inspect the locking function of the nut.

Assembly
IPL Added a optional O-ring for installation of parts into the piston.

32-41-87 Page 2
Jun 30/10
This document is subject to the controls and restrictions on the first page.
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

PAGES DESCRIPTION OF CHANGE

Assembly Deleted the part numbers table for the heat sink installation as operator
verification of disk part numbers is not necessary.

Fits and Clearances Introduced the torque values necessary for the bleeder valve stem during
installation.

Special Tools,
Fixtures, Equipment,
and Consumables Updated the list of aqueous cleaner consumables.

Special Tools,
Fixtures, Equipment,
and Consumables Revised the list for other consumables.

IPL Updated the contact details for HTE part number vendors.

IPL Added data for "True" (Full) part numbers.

IPL Revised the Parts list and added the Numerical Index.

32-41-87 Page 3
Jun 30/10
This document is subject to the controls and restrictions on the first page.
INTENTIONALLY BLANK
AIRCRAFT WHEELS & BRAKES
GOODRICH CORPORATION
101 WACO STREET
P.O. BOX 340
TROY, OHIO 45373
U.S.A.
TEL: 937-339-3811
FAX: 937-440-2055
https://techpubs.goodrich.com

CAGE: 97153

COMPONENT MAINTENANCE MANUAL

WITH
ILLUSTRATED PARTS LIST
MAIN LANDING GEAR BRAKE
ASSEMBLY
PART No. 2-1684

These commodities, software, or technology are controlled by the U.S. Export Administration Regulations
(EAR). Diversion contrary to U.S. law is prohibited. ECCN: 9E991.

32-41-87
REVISION No. 1 TP 1
INITIAL ISSUE : Dec 20/04 Jun 30/10
INTENTIONALLY BLANK
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

RECORD OF REVISIONS

REV ISSUE INSERTED REV ISSUE INSERTED

No. DATE No. DATE
DATE BY DATE BY

0 Dec 20/04
1 Jun 30/10

ROR

32-41-87 Page 1
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INTENTIONALLY BLANK
GOODRICH CORPORATION, A PART OF COLLINS AEROSPACE
COMPONENT MAINTENANCE MANUAL
Part Number 2-1684

RECORD OF TEMPORARY REVISIONS

TEMPORARY AFFECTED DATE PAGES PAGES DATE PAGES PAGES

REVISION PAGE ARE ADDED ADDED ARE REMOVED REMOVED
NUMBER NUMBERS TO MANUAL BY FROM MANUAL BY

32-1 10007, 10008 Dec 5/06 TROY Jun 30/10 TROY

32-2 7020 Jun 27/07 TROY Jun 30/10 TROY
9001, 9002,
32-3 Oct 28/20 TROY
9007
32-4 6004 Feb 22/22 TROY

U.S. Export Classification: EAR 9E991 32-41-87

COLLINS AEROSPACE PROPRIETARY Page RTR-1
Subject to the restriction on the cover page. Feb 22/22
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

RECORD OF TEMPORARY REVISIONS

INSERTED REMOVED
TEMP ISSUE
REV DATE PAGE No.
No. DATE BY DATE BY

32-1 Dec 5/06 Jun 30/10 IDC

32-2 Jun 27/07 Jun 30/10 IDC

RTR

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INTENTIONALLY BLANK
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

SERVICE BULLETIN LIST

R SB INCLUDED DATE
SB/AEB E TITLE ISSUE IN OF
V DATE REVISION INCORPORATION

SL1522 Return procedure for carbon heat Active Jun 30/10

sinks

SL 1854 Shelf-life limits and storage Active Jun 30/10

recommendations for elastomeric
seals and seal assemblies

SL 1914 Warnings on installation of parts that Feb 3/06 Jun 30/10

are not approved by Goodrich

SL 2004 Alternative temperature sensor Mar 22/06 Jun 30/10

SL 2024 Conductivity value for piston Oct 5/05 Jun 30/10

housing

SL 2038 Introduction of an optional O-ring Apr 17/06 Jun 30/10

SL 2048 Introduction of a new paint primer Nov 16/06 Jun 30/10

SL 2086 Introduction of Optional Lubrication No Effect Jun 30/10

Fitting

SL 2087 Inspection for catalytic oxidation Active Jun 30/10

SL 2107 Inspection of bolts Active Jun 30/10

SL 2116 Introduction of an optional adjuster Jun 9/10 Jun 30/10

pin O-ring

SL 2124 Optional retaining ring Apr 15/10 Jun 30/10

SBL

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE SUBJECT PAGE DATE

TRANSMITTAL LETTER 1 Jun 30/10 TESTING AND FAULT

2 Jun 30/10 ISOLATION 1001 Dec 20/04
3 Jun 30/10 1002 Jun 30/10
4 Blank 1003 Jun 30/10
1004 Jun 30/10
TITLE PAGE 1 Jun 30/10 1005 Dec 20/04
2 Blank 1006 Dec 20/04
1007 Dec 20/04
RECORD OF REVISIONS 1 Jun 30/10 1008 Jun 30/10
2 Blank 1009 Jun 30/10
1010 Blank
RECORD OF TEMPORARY
REVISIONS 1 Jun 30/10 DISASSEMBLY 3001 Dec 20/04
2 Blank 3002 Jun 30/10
3003 Jun 30/10
SERVICE BULLETIN LIST 1 Jun 30/10 3004 Jun 30/10
2 Blank 3005 Dec 20/04
3006 Dec 20/04
LIST OF EFFECTIVE PAGES 1 Jun 30/10 3007 Jun 30/10
2 Jun 30/10 3008 Jun 30/10
3 Jun 30/10 3009 Jun 30/10
4 Blank 3010 Jun 30/10
3011 Jun 30/10
TABLE OF CONTENTS 1 Jun 30/10 3012 Jun 30/10
2 Jun 30/10 3013 Jun 30/10
3 Jun 30/10 3014 Blank
4 Blank
CLEANING 4001 Dec 20/04
INTRODUCTION 1 Jun 30/10 4002 Jun 30/10
2 Jun 30/10 4003 Dec 20/04
3 Jun 30/10 4004 Dec 20/04
4 Jun 30/10 4005 Dec 20/04
5 Jun 30/10 4006 Jun 30/10
6 Jun 30/10 4007 Dec 20/04
4008 Blank
DESCRIPTION AND
OPERATION 1 Dec 20/04 INSPECTION/CHECK 5001 Jun 30/10
2 Dec 20/04 5002 Dec 20/04
3 Jun 30/10 5003 Jun 30/10
4 Jun 30/10 5004 Jun 30/10
5 Jun 30/10 5005 Jun 30/10
6 Jun 30/10 5006 Jun 30/10
7 Jun 30/10 5007 Jun 30/10
8 Jun 30/10 5008 Jun 30/10
5009 Jun 30/10
5010 Jun 30/10
5011 Jun 30/10
5012 Jun 30/10

LEP

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
Part Number 2-1684

LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE SUBJECT PAGE DATE

INSPECTION/CHECK ASSEMBLY
(CONTINUED) 5013 Jun 30/10 (CONTINUED) 7010 Jun 30/10
5014 Jun 30/10 7011 Jun 30/10
5015 Jun 30/10 7012 Jun 30/10
5016 Jun 30/10 7013 Jun 30/10
5017 Jun 30/10 7014 Jun 30/10
5018 Jun 30/10 7015 Jun 30/10
5019 Jun 30/10 7016 Jun 30/10
5020 Jun 30/10 7017 Jun 30/10
5021 Jun 30/10 7018 Jun 30/10
5022 Jun 30/10 7019 Jun 30/10
5023 Jun 30/10 7020 Jun 30/10
5024 Jun 30/10 7021 Jun 30/10
5025 Jun 30/10 7022 Jun 30/10
5026 Blank 7022 Jun 30/10

REPAIR 6001 Jun 30/10 FITS AND CLEARANCES 8001 Dec 20/04
6002 Jun 30/10 8002 Dec 20/04
6003 Jun 30/10 8003 Jun 30/10
6004 Jun 30/10 8004 Blank
6005 Jun 30/10
6006 Jun 30/10 SPECIAL TOOLS, FIXTURES,
6007 Jun 30/10 EQUIPMENT AND
6008 Jun 30/10 CONSUMABLES 9001 Dec 20/04
6009 Jun 30/10 9002 Dec 20/04
6010 Jun 30/10 9003 Dec 20/04
6011 Jun 30/10 9004 Dec 20/04
6012 Jun 30/10 9005 Jun 30/10
6013 Jun 30/10 9006 Jun 30/10
6014 Jun 30/10 9007 Jun 30/10
6015 Jun 30/10 9008 Jun 30/10
6016 Jun 30/10 9009 Jun 30/10
6017 Jun 30/10 9010 Jun 30/10
6018 Jun 30/10 9011 Jun 30/10
6019 Jun 30/10 9012 Jun 30/10
6020 Jun 30/10 9013 Jun 30/10
6021 Jun 30/10 9014 Blank
6022 Jun 30/10
STORAGE (INCLUDING
ASSEMBLY 7001 Jun 30/10 TRANSPORTATION) 15001 Dec 20/04
7002 Jun 30/10 15002 Blank
7003 Jun 30/10
7004 Jun 30/10 ILLUSTRATED PARTS LIST 10001 Jun 30/10
7005 Jun 30/10 10002 Jun 30/10
7006 Jun 30/10 10003 Jun 30/10
7007 Jun 30/10 10004 Jun 30/10
7008 Jun 30/10 10005 Jun 30/10
7009 Jun 30/10 10006 Jun 30/10

LEP

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

LIST OF EFFECTIVE PAGES

SUBJECT PAGE DATE SUBJECT PAGE DATE

ILLUSTRATED PARTS LIST

(CONTINUED) 10007 Blank
10008 Jun 30/10
10009 Jun 30/10
10010 Jun 30/10
10011 Jun 30/10
10012 Jun 30/10
10013 Jun 30/10
10014 Jun 30/10
10015 Blank
10016 Jun 30/10
10017 Jun 30/10
10018 Blank

LEP

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TABLE OF CONTENTS
Page
INTRODUCTION
1. Introduction INTRO 1

DESCRIPTION AND OPERATION

1. Description 1
2. Operation 5

TESTING AND FAULT ISOLATION

1. High Pressure Leak Test and Functional Test 1001
2. Fault Isolation 1005
3. Set the Length of the Wear Indicator Pins 1007

SCHEMATIC AND WIRING DIAGRAMS NOT APPLICABLE

DISASSEMBLY
1. Disassembly 3001

CLEANING
1. Cleaning 4001

INSPECTION/CHECK
1. General Inspection / Check 5001

REPAIR
1. Repair 6001

ASSEMBLY
1. Assembly 7001

FITS AND CLEARANCES

1. Fits and Clearances 8001

SPECIAL TOOLS, FIXTURES, EQUIPMENT AND CONSUMABLES

1. Special Tools, Fixtures and Equipment 9001
2. Aqueous Cleaner Consumables 9009
3. Other Consumables 9012

SPECIAL PROCEDURES NOT APPLICABLE

REMOVAL NOT APPLICABLE

INSTALLATION NOT APPLICABLE

SERVICING NOT APPLICABLE

STORAGE (INCLUDING TRANSPORTATION)

1. Storage 15001

TOC

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TABLE OF CONTENTS (Continued)

Page
REWORK NOT APPLICABLE

ILLUSTRATED PARTS LIST

1. Introduction 10001

LIST OF ILLUSTRATIONS
Figure

1 Brake Assembly 2
2 Two Hydraulic Systems in the Piston Housing Assembly 3
3 Internal Parts of a Brake Adjuster Assembly 4
4 EDL® Heat Sink Configurations 6
5 Operation of an Adjuster Assembly 8
1001 Initial Setting of the Wear Indicator Pin Length 1009
3001 Measurement of Wear Indicator Pin Length 3003
3002 Brake Disassembly 3008
3003 Parts of an Adjuster Assembly 3011
3004 Adjuster Disassembly 3012
3005 Exploded View of a Hydraulic Fitting 3013
5001 Drive Slot Inspection (When the heat sink is not fully worn and is installed again) 5004
5002 Permitted Movement of Rotor Clips 5006
5003 Catalytic Oxidation and Local Damage on a Thrust Plate 5007
5004 Catalytic Oxidation and Local Damage on the Outer Diameter of a Stator 5007
5005 Torque Lug Inspection 5009
5006 Inspection of the Static Seal Surface 5010
5007 Locations of Mounting Flange and Lee Plugs 5011
5008 Inspection of a Thrust Plate Assembly 5013
5009 Piston Inspection 5015
5010 Sleeve Inspection 5016
5011 Inspection of Bushings 5017
5012 Adjuster Spring Inspection 5018
5013 Inspection of Adjuster Pins 5019
5014 Temperature Sensor 5020
5015 Hardness Measurement Locations on Parts from an Overheated Brake 5025
6001 The Recommended Diameter of Blend-Repaired Areas 6002
6002 Repair of Torque Lugs 6004
6003 Static Seal Surfaces and Port Locations in a Piston Housing 6007
6004 Repair Plug for the Bleeder Port 6008
6005 Port Configuration in the Repair Plug 6009
6006 Lee Plug Removal 6010
6007 Mask and Paint Limits for the Piston Housing 6014
6008 Expansion Slot Repair Limits on Thrust Plate Assembly 6015
6009 Installation of an Insulator 6016
6010 Piston Repair Limits 6018
6011 Sleeve Repair Limits 6020
6012 Heat Shield Repair 6021
6013 Temperature Sensor Repair 6022
7001 Parts of an Adjuster Assembly 7003
7002 Installation of a Spring in a Piston 7004

TOC

32-41-87
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Page 2
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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TABLE OF CONTENTS (Continued)

Page
7003 Assembly and Installation of the Scraper Ring Assembly 7005
7004 Installation of Parts into the Piston 7006
7005 Color-Code Mark on O-rings (1-165, 2-65) 7006
7006 Installation of the Piston into the Sleeve 7008
7007 Installation of the Adjuster Pin (2-40) 7009
7008 Installation of a Backup Ring on a Sleeve 7011
7009 Sizing Backup Rings on the Sleeve 7012
7010 Lockwire on Adjuster Assemblies 7013
7011 Torque Tube Assembly 7015
7012 Attach the Piston Housing Assembly to the Torque Tube Assembly 7017
7013 Heat Sink Part Locations 7018
7014 Application of Anti-seize Compound 7020
7015 Bolt Torque Sequence for the Installation of the Backplate Assembly 7020
7016 Lockwire Pattern of Bolts (1-70) and Screw (1-60) 7021
8001 Measurement Locations on Parts 8002
9001 Adjuster Assembly / Disassembly Tool 9002
9002 Backup Ring Installation Tool 9003
9003 Backup Ring Sizing Tool 9004
9004 Piston Installation "Support" Tool 9005
9005 Piston Installation "Bullet" Tool 9005
9006 Piston Installation "Guide" Tool 9006
9007 Adjuster Pin Installation Tool 9007
9008 Radial Riveting Peen 9007
9009 Radial Riveting Anvil 9008
9010 High-Pressure Leak Test Shims 9008
1 2-1684 Brake Assembly 10008
2 Adjuster Assembly 10014
3 Hydraulic Fitting 10018

TOC

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

INTRODUCTION

TASK 32-41-87-871-801-A01
1. Introduction

A. General

(1) This manual is written to obey the rules of the Air Transport Association iSpec2200 and the
rules of AECMA Simplified English.

(2) This manual gives maintenance procedures that can keep the brake assembly in an
airworthy condition. An overhaul facility can use other maintenance procedures, but the
maintenance facility is responsible for these other procedures. The facility must make sure
these other procedures are safe, keep the brake assembly airworthy, and obey applicable
government regulations.

(3) A maintenance facility can use the special tools given in this manual or use other tools that
give the same result.

(4) General industry specifications in this manual (for example: MIL, ASTM, SAE) let
maintenance facilities use locally-available materials permitted by a specification. Goodrich
is not responsible for approval of materials controlled by these specifications.

(5) Refer to the TABLE OF CONTENTS for the page numbers of sections and data in the
sections.

(6) All publications for this assembly are available from the Goodrich wheel and brake
publications web site: https://techpubs.goodrich.com

(7) The weights and measurements in this manual are in S.I. (International System of Units)
metric units. U.S. (English) units are shown in parentheses. Metric units have a comma for
the decimal point. English units have a period for the decimal point.

(8) International System of Units (S.I.) and United States (U.S.) standard units and abbreviations
are shown as follows:

INTRO

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

(9) Maintenance Task Oriented Support System (MTOSS) task and subtask identification is
shown in this manual. The maintenance tasks and other data have MTOSS numbers that
supply the data for Electronic Data Processing (EDP). You can ignore the MTOSS numbers
in the printed manual.

(10) Carefully read and obey all CAUTION and WARNING statements in this manual. Refer to the
descriptions of these statements and the NOTE statement that follows:

A "CAUTION" statement is given to prevent damage to equipment.

A "WARNING" statement is given to prevent personal injury or illness.

A "NOTE" statement is given to make a job easier.

INTRO

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

B. TSO Approval

The existence of Technical Standard Order (TSO) approval of the article displaying the required
marking does not automatically constitute the authority to install and use the article on an airplane.
The conditions and tests required for TSO approval of this article are minimum performance
standards. It is the responsibility of those desiring to install this article either on or within a specific
type or class of airplanes to determine that the airplane operating conditions are within the capacity
of the article demonstrated in accordance with the TSO standards. The article may be installed only
if further evaluation by the user/installer documents an acceptable installation and the installation is
approved by the Administrator.

Additional requirements may be imposed based on airplane specifications, wheel and

brake design, and quality control specifications. In-service maintenance, modifications, and use of
replacement components must be in compliance with the performance standards of this TSO, as
well as any additional specific airplane requirements

C. Verification Dates:

Disassembly Testing Assembly

Dec 20/04 Dec 20/04 Dec 20/04
(By Simulation) (By Simulation) (By Simulation)

INTRO

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

D. Replacement Parts Policies

WARNING: REGARDLESS OF ANY FAA APPROVALS OR DEMONSTRATED COMPLIANCE

WITH AIRFRAME MANUFACTURER'S ORIGINAL EQUIPMENT REQUIREMENTS,
GOODRICH DOES NOT WARRANT OR ASSUME THE RISK OF THE
INSTALLATION OF REPLACEMENT PARTS THAT ARE NOT APPROVED BY
GOODRICH FOR INSTALLATION IN A SPECIFIED ASSEMBLY. OPERATORS
WHO USE REPLACEMENT PARTS THAT ARE NOT APPROVED BY GOODRICH
DO SO AT THEIR OWN RISK AND TAKE FULL RESPONSIBILITY FOR ALL
PROPERTY DAMAGE, PERSONAL INJURY, OR DEATH CAUSED BY SUCH
REPLACEMENTS PARTS. USE ONLY GOODRICH-APPROVED REPLACEMENT
PARTS THAT ARE GIVEN IN THE ILLUSTRATED PARTS LIST OF THE
COMPONENT MAINTENANCE MANUAL OR IN SERVICE BULLETINS OR
SERVICE LETTERS THAT ARE ISSUED BY GOODRICH.

CAUTION: GOODRICH ASSUMES NO LIABILITY WHATSOEVER, WHETHER

CONTRACTUAL, WARRANTY, TORT OR OTHERWISE, FOR ANY FEDERAL
AVIATION ADMINISTRATION SANCTIONS, PRODUCT MALFUNCTIONS,
PROPERTY DAMAGE, PERSONAL INJURIES, OR SIMILAR INCIDENTS THAT
OCCUR AFTER SUBSTITUTION OF PARTS THAT ARE NOT APPROVED BY
GOODRICH, OR SUBSTITUTION OF PARTS WITH ALTERATIONS THAT ARE NOT
APPROVED BY GOODRICH MANUALS OR OTHER WRITTEN PROCEDURES
THAT ARE ISSUED BY GOODRICH.

CAUTION: THE USE OF REPLACEMENT PARTS THAT ARE NOT APPROVED BY GOODRICH
FOR INSTALLATION IN A SPECIFIED ASSEMBLY WILL AUTOMATICALLY VOID
ALL WARRANTIES EXTENDED BY GOODRICH.

The Federal Aviation Administration (FAA) has approved replacement parts that are
different from specified parts in applicable Goodrich publications. Goodrich has not done
tests on these FAA-approved parts and does not give approval for the installation of
these parts.

Goodrich uses proprietary design procedures and rigorous tests to show that Goodrich
assemblies give specified performance or better-than-specified performance. Tests were
done with Goodrich-approved parts in each assembly to show that related subsystems
correctly work together as a system for qualification and certification. Some examples of
related subsystems include: landing gear, brake control (anti-skid), wheels, brakes, and
tires.

Goodrich makes wheel assemblies and brake assemblies to aircraft manufacturer

specifications, to FAA requirements, and to all other applicable regulations. Goodrich
design procedures also use data on wear distribution, thermal balance, dynamic stability,
reliability, endurance, torque sensitivity, and environmental exposure. The environmental
exposure includes: humidity, icing, salt fog, shock, and vibration. Installation of parts that
do not have equivalent design procedures or test results can decrease the performance
of wheel assemblies, brake assemblies, or related subsystems.

FAA approval of replacement parts in Goodrich assemblies usually is given after tests
that are less extensive than performance tests by the aircraft manufacturer and by
Goodrich. The Aircraft Flight Manual, Component Maintenance Manuals, and warranties
are based on performance tests by the aircraft manufacturer and by Goodrich. The
operation of each subsystem depends on all related subsystems to give safe and reliable take-offs
and landings. When equivalent tests with FAA-approved parts are not done,

Goodrich cannot make sure that the assemblies give safe and reliable performance.
INTRO

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

E. Warnings for the Full Manual

WARNING: OBEY TORQUE LIMITS AND OTHER SPECIFIC VALUES THAT ARE GIVEN IN
THIS MANUAL. THESE LIMITS AND VALUES THAT ARE NOT OBEYED CAN
CAUSE PROPERTY DAMAGE, PERSONAL INJURY, OR DEATH.

WARNING: BEFORE YOU USE CHEMICALS, READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE CHEMICALS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CHEMICALS MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN SAFETY
INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES INSTRUCTIONS ON HOW
YOU MUST SAFELY USE, KEEP, AND DISCARD CHEMICALS. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON HOW YOU MUST SAFELY USE,
KEEP, AND DISCARD CHEMICALS.

(1) Cadmium

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

SWALLOWED CAN CAUSE KIDNEY OR REPRODUCTIVE SYSTEM
DISEASE. AFTER YOU TOUCH CADMIUM PLATED PARTS, CLEAN YOUR
HANDS BEFORE YOU EAT OR SMOKE. GET SAFETY INSTRUCTIONS
FROM YOUR EMPLOYER. OBEY GOVERNMENT AND OSHA
REGULATIONS WHEN YOU DISCARD THE PARTS THAT CONTAIN
CADMIUM.

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

PARTICLES, FUMES, OR DUST CAN CAUSE LUNG OR KIDNEY DISEASE.
IF MAINTENANCE PROCEDURES MAKE CADMIUM PARTICLES, FUMES,
OR DUST, TELL YOUR EMPLOYER TO SUPPLY RESPIRATORS,
VENTILATION, AND/OR PROCEDURES TO PREVENT EXPOSURE TO
PERSONNEL.

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

(a) Obey the warnings above before you touch or do maintenance on the parts that are
cadmium plated. Refer to the ILLUSTRATED PARTS LIST to identify the parts that
can be cadmium plated. The Occupational, Safety, and Health Administration (OSHA)
sets mandatory limits on exposure to cadmium dust (29 CFR 1910.1027).

INTRO

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

F. Specification Sources

(1) Get Federal and MIL specifications that are referred to in this manual from the source that
follows:

DAPS
Assist
Building 4/D
700 Robbins Avenue
Philadelphia, Pennsylvania 19111
U.S.A.

Tel: 215-697-6257
Web: http://assist.daps.dla.mil/online/start/

(2) Get AMS specifications that are referred to in this manual from the source that follows:

SAE Customer Service

400 Commonwealth Drive
Warrendale, Pennsylvania 15096-0001
U.S.A.

Tel: 724-776-4970
Fax: 724-776-0790
Web: www.sae.org

(3) Get ASTM specifications that are referred to in this manual from the source that follows:

American Society for Testing and Materials (ASTM)

100 Barr Harbor Drive
West Conshohocken, Pennsylvania 19428
U.S.A.

Tel: 610-832-9500
Web: www.astm.org

INTRO

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

DESCRIPTION AND OPERATION

TASK 32-41-87-870-801-A01
1. Description

A. General

(1) The aircraft hydraulic system operates the brake assembly (brake) with NSA 307-110
hydraulic fluid. The maximum operation pressure is 207 bar (3000 psi).

(2) The piston housing assembly has two hydraulic systems. Each system has one hydraulic
fitting, one bleeder valve, and seven adjuster assemblies (refer to Figure 1). The adjuster
assemblies engage and release the brake assembly. The two hydraulic systems are not
connected (refer to Figure 2).

One hydraulic system pressurizes the brake to stop the airplane. The other
system pressurizes the brake when the airplane is parked or when the primary
system does not operate. It is possible to interchange the connections and the
function of the two hydraulic systems.

B. Description of the Thrust Plate Assembly

(1) The thrust plate assembly (thrust plate) has drive slots on the inner diameter that engage
lugs on the torque tube. The thrust plate does not turn, but slides on the torque tube as
necessary as the brake assembly operates. The thrust plate decreases the transfer of brake
heat to the adjuster assemblies and to the piston housing.

C. Description of the Torque Tube and the Back Plate Assembly

(1) The torque tube and back plate assembly holds the thrust plate, the end plates, and the
stators in correct alignment with the rotors. Ten lugs on the torque tube transfer brake torque
from the end plates and stators to the torque tube.

(2) Three bolts attach the inner flange of the torque tube to an axle flange. Studs in the torque
tube flange transfer brake torque to the axle flange.

(3) A heat shield in the torque tube decreases the transfer of brake heat to the axle.

(4) The back plate pads decrease the transfer of brake heat to the back plate.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

CARBON HEAT SINK

BACK PLATE
BLEEDER VALVE ASSEMBLY

WEAR
INDICATOR PIN ROTOR
ASSEMBLIES
HYDRAULIC
FITTING TORQUE TUBE
HEAT
SHIELD
END PLATE
ASSEMBLIES
STUD

PISTON
HOUSING
ASSEMBLY
SHOULDER
SCREW

TEMPERATURE STATOR
SENSOR ASSEMBLIES
ADJUSTER THRUST
ASSEMBLY PLATE ASSEMBLY

THRUST PLATE
SLEEVE ASSEMBLY BACK PLATE PAD
PISTON PISTON
HOUSING BACK
PLATE

TEMPERATURE
SENSOR TORQUE TUBE
HEAT SHIELD
AXLE
FLANGE

Brake Assembly
Figure 1 /GRAPHIC 32-41-87-991-001-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Two Hydraulic Systems in the Piston Housing Assembly

Figure 2 /GRAPHIC 32-41-87-991-002-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

D. Description of Adjuster Assemblies

(1) Each adjuster assembly contains the parts that are shown in Figure 3.

O-RING
(NOT PART OF
PIN RETAINER BACKUP RING
ADJUSTER ASSEMBLY)
BACKUP SPRING GUIDE
RING BUSHING O-RING
SCRAPER RING
O-RING BALL

SEAL SNAP RING

RETAINER
ADJUSTER
PIN
O-RING NUT

COVER
RETAINING
RING INSTRUCTION
PLATE
BACKUP
RINGS SPRING
PISTON SLEEVE
ADJUSTER
TUBE RETAINING
RING

Internal Parts of a Brake Adjuster Assembly

Figure 3 /GRAPHIC 32-41-87-991-003-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

E. Description of the Heat Sink

(1) The heat sink contains carbon disks with friction surfaces that cause the brake to stop the
rotation of the wheel. The friction surfaces are on the disks as follows:

(a) Two end plate assemblies (end plates) have drive slots on the inner diameter that
engage lugs on the torque tube. Metal clips on the end plates give protection to each
drive slot. The end plates do not turn, but slide as necessary on the torque tube as the
brake operates.

(b) Four rotor assemblies (rotors) have drive slots on the outer diameter that engage drive
inserts on the inner wheel half. Metal clips on the rotors give protection to each drive
slot. The rotors turn with the wheel, and slide as necessary on the drive inserts of the
wheel as the brake operates.

(c) Three stator assemblies have drive slots on the inner diameter that engage lugs on
the torque tube. Metal clips on the stators give protection to each drive slot. The
stators do not turn, but slide on the torque tube as necessary as the brake assembly
operates. One stator is between each two rotors.

(2) The heat sink is an EDL® configuration, with rotors and stators that have much different
thicknesses (refer to Figure 4). When this brake has sufficient wear to make the wear
indicator pins flush, a complete replacement heat sink is installed.

(3) A replacement heat sink can contain new disks, "second-run" disks, or a mixture of these
disks. Goodrich machines worn thick disks to make second-run disks.

(4) A mixture of brakes with factory-built or replacement heat sinks are permitted on an airplane.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

EDL® Heat Sink Configurations

Figure 4 /GRAPHIC 32-41-87-991-004-A01

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TASK 32-41-87-870-802-A01
2. Operation

A. Operation of the Heat Sink

(1) Pressurized hydraulic fluid pushes the pistons against the thrust plate. The thrust plate
compresses the rotors and stators between the two end plates (refer to Figure 1). These
compressed parts cause friction between the rotors, which turn with the wheel, and the end
plates and stators, which cannot turn.

B. Operation of the Adjuster Assemblies

(1) When the brake assembly is operated, each piston compresses the spring between the
piston and the spring guide. Refer to Figure 5. The adjuster pin, the ball, and the adjuster
tube hold the spring guide in position. If the piston moves only a sufficient distance to touch
the spring guide, the adjuster parts are not affected.

(2) Wear of the heat sink causes more movement of the piston after it touches the spring guide.
This causes the piston to push the spring guide and adjuster tube to a new position on the
ball. When hydraulic pressure is decreased, the springs push the pistons back. The pistons
return the same distance as the initial distance between the piston and the end of the spring
guide. This distance between the pistons and the thrust plate assembly is the "running
clearance".

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Operation of an Adjuster Assembly

Figure 5 /GRAPHIC 32-41-87-991-005-A01

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TESTING AND FAULT ISOLATION

TASK 32-41-87-700-801-A01
1. High Pressure Leak Test and Functional Test

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

NOTE: Refer to the SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLES section
for full data on special tools.

(1) Tools, fixtures, and equipment

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE MIN. QTY. DESCRIPTION

Local Purchase 1 Hydraulic pressure source (345 bar (5000 psi)

min. capacity)

HTE711-59 1 Hydraulic fitting

114-330 1 set Shims (special tool)

Locally Make As Necessary Protective shields

(2) Consumables

NOTE: Equivalent alternatives are not permitted for the hydraulic fluid.

REFERENCE DESCRIPTION

NSA 307-110 Hydraulic fluid

(3) Referenced information

Not applicable

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PART No. 2-1684

C. Job Set-up

Subtask 32-41-87-700-001-A01

(1) Preparation (Refer to IPL Figure 1)

WARNING: BEFORE YOU USE HYDRAULIC FLUID, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE FLUID. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
HYDRAULIC FLUID MAY CAUSE INJURY TO YOU OR MAKE YOU SICK
WHEN YOU DO NOT OBEY SAFETY INSTRUCTIONS. THE MSDS TELLS
HOW YOU MUST SAFELY USE, KEEP, AND DISCARD HYDRAULIC FLUID.
GET INSTRUCTIONS FROM YOUR EMPLOYER THAT TELL HOW YOU
MUST SAFELY USE, KEEP, AND DISCARD HYDRAULIC FLUID.

WARNING: REMOVE HYDRAULIC FLUID THAT FALLS ON BRAKE PARTS (REFER TO

THE CLEANING SECTION). HYDRAULIC FLUID CAN CAUSE DAMAGE TO
PAINTED SURFACES AND CAN CAUSE CONTAMINATION OF CARBON
PARTS.

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT YOU

SWALLOW CAN CAUSE KIDNEY OR REPRODUCTIVE SYSTEM DISEASE.
AFTER YOU TOUCH PARTS THAT CONTAIN CADMIUM, CLEAN YOUR
HANDS BEFORE YOU EAT OR SMOKE. GET SAFETY INSTRUCTIONS
FROM YOUR EMPLOYER. OBEY GOVERNMENT AND OSHA
REGULATIONS WHEN YOU DISCARD THE PARTS THAT CONTAIN
CADMIUM.

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE

(a) Put the brake in the same position as the brake position on the airplane.

WARNING: MAKE SURE ROTORS ARE ALIGNED AND/OR SUPPORTED TO

PREVENT DAMAGE TO STATORS.

(b) Fill the two hydraulic systems with NSA 307-110 hydraulic fluid.

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PART No. 2-1684

D. Test Procedures

Subtask 32-41-87-700-002-A01

(1) High-pressure leak test (Refer to IPL Figure 1 and IPL Figure 2)

NOTE: The high-pressure leak test is only necessary after you replace a Lee plug in the
piston housing assembly.

(a) Put shims between the thrust plate assembly (1-125) and the end plate assembly of
the carbon heat sink.

WARNING: DO NOT PRESSURIZE THE TWO HYDRAULIC SYSTEMS AT THE SAME

TIME. THIS CAN CAUSE DAMAGE TO THE BRAKE ASSEMBLY AND CAN
CAUSE IT TO EJECT PARTS OR HYDRAULIC FLUID.

WARNING: DO NOT PRESSURIZE THE HYDRAULIC SYSTEM TO MORE THAN THE

SPECIFIED MAXIMUM PRESSURE. MORE PRESSURE THAN THE
MAXIMUM PRESSURE CAN CAUSE DAMAGE TO THE BRAKE
ASSEMBLY AND CAN CAUSE IT TO EJECT PARTS OR HYDRAULIC
FLUID.

WARNING: DO NOT DO THE HIGH PRESSURE LEAK TEST WITHOUT PROTECTIVE

SHIELDS AROUND THE BRAKE ASSEMBLY. THIS TEST CAN CAUSE THE
BRAKE ASSEMBLY TO EJECT PARTS OR HYDRAULIC FLUID.

(b) Put protective shields around the brake assembly.

(c) Pressurize one hydraulic system to 310,26 - 314 bar (4500 - 4550 psi). Keep this
pressure for five minutes. Refer to paragraph 2 if you see a leak.

(d) Decrease the pressure to 0,0 bar (0.0 psi) and make sure that the pistons (2-115)
move away from the thrust plate assembly.

(e) Pressurize the other hydraulic system to 310,26 - 314 bar (4500 - 4550 psi). Keep this
pressure for five minutes. Refer to paragraph 2 if you see a leak.

(f) Decrease the pressure to 0,0 bar (0.0 psi) and make sure that the pistons move away
from the thrust plate assembly.

(g) Remove the shims.

(h) Do the functional test (refer to paragraph 1.D.(2)).

(Ref.: Subtask 32-41-87-700-003-A01).

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PART No. 2-1684

Subtask 32-41-87-700-003-A01

(2) Functional test (Refer to IPL Figure 1)

NOTE: This procedure gives function and leakage tests of repaired and overhauled brake
assemblies.

(a) Turn the brake assembly to put the piston housing assembly (1-205) at the top.

WARNING: DO NOT PRESSURIZE THE TWO HYDRAULIC SYSTEMS AT THE SAME

TIME. THIS CAN CAUSE DAMAGE TO THE BRAKE ASSEMBLY AND CAN
CAUSE IT TO EJECT PARTS OR HYDRAULIC FLUID.

WARNING: DO NOT PRESSURIZE THE HYDRAULIC SYSTEM TO MORE THAN THE

SPECIFIED MAXIMUM PRESSURE. MORE PRESSURE THAN THE
MAXIMUM PRESSURE CAN CAUSE DAMAGE TO THE BRAKE
ASSEMBLY AND CAN CAUSE IT TO EJECT PARTS OR HYDRAULIC
FLUID.

(b) Pressurize one of the two hydraulic systems to 206,8 - 210,3 bar (3000 - 3050 psi).
Keep this pressure for five minutes. Refer to paragraph 2 if you see a leak. Decrease
the pressure to 0,0 bar (0.0 psi).

(d) Decrease the pressure to 15,2 - 17,2 bar (220 - 250 psi). Try to turn the top rotor by
hand. Reject the brake assembly if you can turn the top rotor.

(e) Decrease the pressure to 8,3 - 10,0 bar (120 - 145 psi). Try to turn the top rotor by
hand. If you cannot turn the top rotor, refer to paragraph 2.

(f) Decrease the pressure to 6,9 - 7,9 bar (100 - 115 psi). Measure the distance between
each piston and the insulator (1-130) in the thrust plate assembly (1-125). If a distance
is less than 1,14 mm (0.045 inch), refer to paragraph 2.

(g) Operate the brake for five cycles from 0,0 to 68,9 bar (0.0 to 1000 psi). If a piston does
not fully retract when the pressure is 0,0 bar, refer to paragraph 2.

(h) Do the functional test again for the other hydraulic system (refer to paragraphs
1.D.(2)(a) - (g)).

NOTE: Keep the pressure source connected to the brake to set the length of the wear
indicator pins (1-115) (refer to paragraph 3).
(Ref.: TASK 32-41-87-820-801-A01).

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PART No. 2-1684

TASK 32-41-87-810-801-A01
2. Fault Isolation

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

(1) Tools, fixtures, and equipment

Not applicable

(2) Consumables

Not applicable

(3) Referenced information

REFERENCE REASON

INSPECTION/CHECK section To get full inspection procedures

FITS AND CLEARANCES section To get torques

REPAIR section To get full repair procedures

C. Job Set-up

Not applicable

D. Procedure (Refer to IPL Figure 1 and IPL Figure 2)

Subtask 32-41-87-810-002-A01

POSSIBLE CAUSES OF LOSS OF

CORRECTION
HYDRAULIC FLUID
Worn or damaged O-rings (1-165, 1-185, Replace defective parts.
1-195, 2-65, 2-85) or backup rings
(2-5, 2-70, 2-90)
Loose bleeder valve (1-175) or hydraulic Tighten a loose bleeder valve or a loose hydraulic
fitting (1-190) fitting to the correct torque. A bleeder valve can be
cadmium plated.
Damaged Piston (2-115). Repair or replace defective parts.
Damaged inner diameter or outer sealing
surface of the
sleeve (2-50)

Damaged sealing surface of the adjuster

pin (2-40)

Loose Lee plug (1-215)

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PART No. 2-1684

POSSIBLE CAUSES FOR LESS THAN

MINIMUM RUNNING CLEARANCE WITH
CORRECTION
7,9 BAR (115 PSI) APPLIED HYDRAULIC
PRESSURE

Weak springs (2-110) Measure the strength of the springs. Replace

defective springs.

Self-locking nut (2-25) is loose or missing Tighten a loose nut to the correct torque. Replace
a nut that is missing. A nut can be cadmium plated.

POSSIBLE CAUSES FOR A BRAKE THAT

CORRECTION
DRAGS OR OVERHEATS

Too much back-pressure in the hydraulic Repair or adjust the hydraulic system (refer to the
system applicable manual for the procedure)

Weak springs (2-110) Measure the strength of the springs. Replace

defective springs.

Air in the hydraulic system Bleed air from the piston housing or the hydraulic
system. (refer to the applicable manual for the
procedure)

Self-locking nut (2-25) is loose or missing Tighten a loose nut to the correct torque. Replace
a nut that is missing. A nut can be cadmium
plated.

Adjuster tubes (2-35) have a crack or are Replace defective parts.

too soft

Broken adjuster pins (2-40)

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PART No. 2-1684

TASK 32-41-87-820-801-A01
3. Set the Length of the Wear Indicator Pins (1-115) (Refer to IPL Figure 1)

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

(1) Tools, fixtures, and equipment

NOTE: Refer to the SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLES

section for full data on special tools.

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE MIN. QTY. DESCRIPTION

Local Purchase 1 Hydraulic pressure source (345 bar (5000 psi)

min. capacity)

HTE711-59 1 Hydraulic fitting

(2) Consumables

REFERENCE DESCRIPTION

NSA 307-110 Hydraulic fluid

(3) Referenced information

Not applicable

C. Job Set-up

Not applicable

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PART No. 2-1684

D. Procedure

Subtask 32-41-87-820-001-A01

(1) Cut the wear indicator pins (Refer to IPL Figure 1 and IPL Figure 3)

WARNING: DO NOT PRESSURIZE THE TWO HYDRAULIC SYSTEMS AT THE SAME

TIME. THIS CAN CAUSE DAMAGE TO THE BRAKE ASSEMBLY AND CAN
CAUSE IT TO EJECT PARTS OR HYDRAULIC FLUID.

WARNING: DO NOT PRESSURIZE THE HYDRAULIC SYSTEM TO MORE THAN THE

SPECIFIED MAXIMUM PRESSURE. MORE PRESSURE THAN THE
MAXIMUM PRESSURE CAN CAUSE DAMAGE TO THE BRAKE
ASSEMBLY AND CAN CAUSE IT TO EJECT PARTS OR HYDRAULIC
FLUID.

(a) Connect a hydraulic supply hose to one of the two hydraulic systems in the brake.

(b) Pressurize the brake to 99,9 - 103,4 bar (1450 - 1500 psi).

NOTE: Do not change the wear pin length on a brake that is not fully worn and you
can install on an airplane.

(d) Decrease the pressure to 0,0 bar (0.0 psi).

(e) Disconnect the brake and install a protective cap (3-5) on each hydraulic
fitting (1-190).

(f) You can apply an optional corrosion-prevention paint to the cut end of each wear
indicator pin.

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PART No. 2-1684

WEAR INDICATOR PIN

CUT THE PIN TO A LENGTH

OF 52,6 - 54,1 MM
(2.07 - 2.13 INCHES)

PISTON HOUSING

Initial Setting of the Wear Indicator Pin Length

Figure 1001 /GRAPHIC 32-41-87-991-101-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

DISASSEMBLY

TASK 32-41-87-030-801-A01
1. Disassembly

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

(1) Tools, fixtures, and equipment

NOTE: Refer to the SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLES

section for full data on special tools.

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE MIN. QTY. DESCRIPTION

Local Purchase 1 Hydraulic pressure source (345 bar (5000 psi) min.
capacity)

HTE711-59 1 Hydraulic fitting

114-291 1 Adjuster assembly/disassembly tool (special tool)

(2) Consumables

NOTE: Equivalent alternatives are not permitted for the hydraulic fluid.

REFERENCE DESCRIPTION

Airbus Material Specification NSA 307.110 Hydraulic fluid

(3) Referenced information

Not applicable

32-41-87 Page 3001

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

C. Job Set-up

Subtask 32-41-87-030-001-A01

(1) Preparation (Refer to IPL Figure 1)

WARNING: BEFORE YOU USE HYDRAULIC FLUID, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE FLUID. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
HYDRAULIC FLUID MAY CAUSE INJURY TO YOU OR MAKE YOU SICK
WHEN SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD
HYDRAULIC FLUID. GET INSTRUCTIONS FROM YOUR EMPLOYER ON
HOW YOU MUST SAFELY USE, KEEP, AND DISCARD HYDRAULIC FLUID.

WARNING: DO NOT PRESSURIZE THE TWO HYDRAULIC SYSTEMS AT THE SAME

TIME. TWO PRESSURIZED SYSTEMS CAN CAUSE DAMAGE TO THE
BRAKE ASSEMBLY AND CAN CAUSE THE BRAKE TO EJECT PARTS OR
HYDRAULIC FLUID.

WARNING: DO NOT PRESSURIZE A HYDRAULIC SYSTEM TO MORE THAN THE

SPECIFIED PRESSURE. TOO MUCH PRESSURE CAN CAUSE DAMAGE
TO THE BRAKE ASSEMBLY AND CAN CAUSE THE BRAKE TO EJECT
PARTS OR HYDRAULIC FLUID.

CAUTION: MAKE SURE THAT CARBON PARTS DO NOT HIT HARD SURFACES.
CARBON PARTS ARE EASILY DAMAGED.

CAUTION: DO NOT LET HYDRAULIC FLUID, OIL, GREASE, PAINT, PAINT REMOVAL
CHEMICALS, AND MOST SOLVENTS TOUCH CARBON PARTS.
CONTAMINATION CAN CAUSE DAMAGE TO CARBON PARTS.

(a) Pressurize one of the two hydraulic systems of the brake to 99,9 - 103,4 bar
(1450 - 1500 psi).

(b) Measure the length of each wear indicator pin (1-115) from the piston housing
assembly (1-205) as shown in Figure 3001. Measure to the nearest 0,8 mm
(1/32 inch) on the shortest wear indicator pin.

(c) Record the length of wear indicator pins and other data on a CARBON RETURN
DATA FORM (refer to Goodrich Service Letter 1522).

(d) Decrease the pressure to 0,0 bar (0.0 psi).

(e) Disconnect the hydraulic fluid supply hose.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

WEAR INDICATOR PIN

LENGTH OF WEAR
INDICATOR PIN

PISTON HOUSING

Measurement of Wear Indicator Pin Length

Figure 3001 /GRAPHIC 32-41-87-991-301-A01

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PART No. 2-1684

D. Procedure

Subtask 32-41-87-030-002-A01

(1) Heat sink removal (Refer to IPL Figure 1)

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

(a) Put the brake assembly on a work surface with the piston housing assembly (1-205) at
the top.

CAUTION: DO NOT PUT OTHER BRAKE PARTS ON A REMOVED TEMPERATURE

SENSOR. A SENSOR IS EASILY DAMAGED.

(b) Cut the lockwire (1-55), remove the cap screw (1-60), and remove the temperature
sensor (1-65). The cap screw can be cadmium plated.

(d) Cut the lockwire (1-55) and remove the bolts (1-70). Remove the back plate
assembly (1-75).

(e) Remove the heat sink (1-105) from the torque tube.

NOTE: Lift a stator assembly and a rotor assembly together for easier disassembly.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

(f) Send fully-worn or damaged heat sinks to a Goodrich Wheel and Brake Service
Center. Refer to Goodrich Service Letter 1522 for more data about the carbon return
policy.

NOTE: Do not change the length of the wear indicator pins in a brake assembly which
does not receive a new heat sink.

NOTE: If you install the used carbon parts again, identify each part to make sure that
it is installed in the same position. All friction surfaces must touch the same
friction surfaces of mating parts that they touched before the parts were
removed. The drive slots must align with the same drive slots in other carbon
parts. Do not turn a part to a different position. Use tape or a felt-tip marker to
make identification marks on the outer diameter of the parts. These marks
must show the position of the part (1, 2, 3, or 4) and which side of each part
points to the piston housing.

Put the carbon parts in shipping crates that Goodrich supplies when the
crates are available. Each crate has molded inserts that give protection to
each carbon part. You can send the parts in other containers that do not
let the parts move. These other containers must not let the parts touch
other parts or touch hard surfaces.

Data about the shipment is necessary for Customs department in each

country. The shipping papers must include the data that follows:

1 The part numbers of the parts in the shipment.

2 The material given as:

"8803.30.0010 Civil Aircraft Carbon Brakes, Used"

and
NMFC Item 11920, Class 100.

3 The quantity of containers and the quantity of parts in the shipment.

4 The statement: "U.S. MANUFACTURED GOODS BEING RETURNED."

5 The value of the parts (10% of the value in the current price list) (for use only by
the Customs department).

6 CARBON RETURN DATA FORM(S).

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-030-003-A01

(2) Thrust plate assembly (1-125) disassembly (Refer to IPL Figure 1)

(a) Remove the cotter pins (1-110), adapters (1-120), and wear indicator pins (1-115)
from the thrust plate assembly (1-125). The cotter pins (1-110) can be cadmium
plated.

Subtask 32-41-87-030-004-A01

(3) Piston housing assembly (1-205) removal (Refer to IPL Figure 1)

(a) Remove the three nuts (1-145), washers (1-150), and shoulder screws (1-155).

(b) Remove the piston housing assembly (1-205) from the torque tube (1-160).

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-040-001-A01

(4) Piston housing assembly (1-205) disassembly (Refer to IPL Figure 1 and IPL Figure 2)

WARNING: DO NOT PUSH PISTONS INTO THE PISTON HOUSING ASSEMBLY

BEFORE DRAIN TUBES ARE CONNECTED.

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

(a) Remove the two hydraulic fittings (1-190) and O-rings (1-195) from the piston housing
assembly (1-205). Discard the O-rings.

(b) Remove the two bleeder valves (1-175) and O-rings (1-185). The bleeder valves can
be cadmium plated. Discard the O-rings.

(c) Install temporary drain tubing at the inlet and bleeder ports, or use other procedures to
make sure that the drained hydraulic fluid goes into a waste fluid container.

(d) Push each piston (2-115) fully into the piston housing assembly to push out the
hydraulic fluid.

(e) Cut the lockwire and remove the adjuster assemblies (1-170).

(f) Drain the hydraulic fluid from the piston housing assembly.

(g) If you must remove the identification plates (1-200, 1-210), record the location of each
plate. Record the data that is shown on each plate.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

BACK PLATE
ASSEMBLY (1-75)

BOLT (1-70)

HEAT SINK (1-105)

WEAR INDICATOR THRUST PLATE

PIN (1-115) ASSEMBLY (1-125)
ADAPTER (1-120)
ADJUSTER
ASSEMBLY
O-RING (1-195) (1-170)
HYDRAULIC FITTING (1-190)
PISTON HOUSING
NUT (1-145) ASSEMBLY (1-205)
WASHER (1-150)

BLEEDER VALVE (1-175) HEAT SHIELD

O-RING (1-185) (1-100)
TORQUE
IDENTIFICATION TUBE (1-160)
PLATE (1-200)
WASHER
(1-30)
NUT (1-25)
BOLT
RETAINER TEMPERATURE
(1-15) SENSOR (1-65)
BOLT
NUT (1-40) (1-20) CAP SCREW (1-60)
WASHER
(1-45) SHOULDER SCREW
WASHER (1-155)
(1-10)
STUD
(1-50) NUT (1-5)

SCREW (1-35)

Brake Disassembly
Figure 3002 /GRAPHIC 32-41-87-991-302-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-030-005-A01

(5) Torque tube (1-160) disassembly (Refer to IPL Figure 1)

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

(a) Remove the heat shield (1-100).

(b) Remove the nuts (1-40), washers (1-45), and studs (1-50) when they are damaged
(the studs are a press-fit in the torque tube).

(c) Remove the nuts (1-25), washers (1-30), screws (1-35), bolt retainers (1-15),
nuts (1-5), and bolts (1-20). The nuts (1-5, 1-25), bolts (1-20), and screws (1-35) can
be cadmium plated.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-030-006-A01

(6) Adjuster assembly (1-170) disassembly (Refer to IPL Figure 1 and IPL Figure 2)

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

(a) Remove the nut (2-25) from the adjuster pin (2-40). Push the piston (2-115) into the
sleeve (2-50) if necessary to get access to the nut. Refer to Figure 3003. The nut can
be cadmium plated.

(b) Pull the adjuster tube (2-35) and ball (2-30) out of the adjuster assembly. Push the ball
out of the adjuster tube.

NOTE: Replace the adjuster tubes at each overhaul or heat sink change.

(c) Push the piston (2-115) out of the sleeve (2-50).

(d) Pull the pin retainer (2-45) to remove the pin retainer and the adjuster pin (2-40) from
the piston. The pin retainer can be cadmium plated.

CAUTION: DO NOT USE SHARP OR HARD TOOLS TO REMOVE O-RINGS AND

BACKUP RINGS. SHARP OR HARD TOOLS CAN CAUSE DAMAGE TO
PARTS.

(e) Remove the O-ring (1-165) from the sleeve. Discard the O-ring.

NOTE: Use the blunt end of a wooden, brass, plastic (or equally soft) tool to remove
the O-rings.

(f) Remove the backup ring (2-5) when it is damaged.

NOTE: Use the blunt end of a wooden, brass, plastic (or equally soft) tool to remove
the backup rings.

(g) Remove scraper rings (2-55) and backup rings (2-70) when they are damaged.
Remove a O-ring (2-60) when you remove the scraper ring (2-55) in the same sleeve.

(h) Remove the O-ring (2-65) from the piston. Discard the O-ring.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

(i) Remove the retaining ring (2-75), seal retainer (2-80), backup rings (2-90),
O-ring (2-85), and bushing (2-95) from the piston. The retaining ring (2-75) can be
cadmium plated. Discard the O-ring and the backup rings.

(j) Remove the snap ring (2-10), cover (2-15), and instruction plate (2-20) from the
piston.

O-RING

O-RING (2-60)

O-RING

O-RING
(2-85)

Parts of an Adjuster Assembly

Figure 3003 /GRAPHIC 32-41-87-991-303-A01

WARNING: OBEY THE INSTRUCTIONS TO REMOVE THE SPRING IN EACH

ADJUSTER ASSEMBLY. THE SPRING IS COMPRESSED UNDER HIGH
LOAD. IF YOU DO NOT REMOVE THE SPRING WITH CORRECT
EQUIPMENT OR DO NOT OBEY THE INSTRUCTIONS, PARTS CAN BE
EJECTED AND CAUSE INJURY TO PERSONNEL.

(k) Put the piston and the special tool in a drill press or arbor press as shown in
Figure 3004.

(l) Push down on the spring guide (2-105) until the spring guide does not touch the
retaining ring (2-100). Lock the press and remove the retaining ring.

(m) Push down on the spring guide again and unlock the press. Slowly release pressure
on the spring guide until compression is released from the spring (2-110). Remove the
spring guide and spring.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Adjuster Disassembly
Figure 3004 /GRAPHIC 32-41-87-991-304-A01

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PART No. 2-1684

Subtask 32-41-87-030-007-A01

(7) Hydraulic fitting (1-190) disassembly (Refer to IPL Figure 1 and IPL Figure 3)

NOTE: Disassemble the hydraulic fitting to replace the O-rings (3-15, 3-30) only when the
hydraulic fitting leaks.

(a) Remove the nipple (3-10) from the nipple end (3-35). Refer to Figure 3005.

(b) Remove the O-rings (3-15, 3-30).

NOTE: It is not necessary to remove the nipple to replace the O-ring (3-30). Push the
nipple valve (3-25) down, pull the O-ring out, and carefully install a new
O-ring. Remove pressure from the nipple valve.

NIPPLE NIPPLE O-RING (3-30)

END (3-35) VALVE (3-25)

SPRING (3-20) O-RING (3-15) NIPPLE (3-10)

Exploded View of a Hydraulic Fitting

Figure 3005 /GRAPHIC 32-41-87-991-305-A01

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

CLEANING

TASK 32-41-87-100-801-A01
1. Cleaning

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

(1) Tools, fixtures, and equipment

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE MIN. QTY. DESCRIPTION

Local Purchase 1 Parts washer (for solvents)

Local Purchase 1 Parts washer (for aqueous cleaning chemicals)

Local Purchase 1 Media blast equipment for plastic media

Local Purchase 1 Media blast equipment for steel grit media

Local Purchase 1 Oven (with ceramic spacers or graphite spacers)

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

(2) Consumables

NOTE: Equivalent alternatives are permitted for the items in the list that follows.

WARNING: BEFORE YOU USE A SPECIFIED CLEANING PRODUCT, READ,

UNDERSTAND, AND OBEY ALL SAFETY INSTRUCTIONS FOR THE
CLEANING PRODUCT. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS
FROM THE MANUFACTURER, THE MATERIAL SAFETY DATA SHEET
(MSDS), AND GOVERNMENT REGULATIONS. A CLEANING PRODUCT
MAY CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN YOU DO NOT
OBEY SAFETY INSTRUCTIONS. THE MSDS TELLS HOW YOU MUST
SAFELY USE, KEEP, AND DISCARD A CLEANING PRODUCT. GET
INSTRUCTIONS FROM YOUR EMPLOYER THAT TELL HOW YOU MUST
SAFELY USE, KEEP, AND DISCARD A CLEANING PRODUCT.

REFERENCE DESCRIPTION

Local Purchase Solvent, butyl alcohol

Local Purchase Solvent, isopropyl alcohol

MIL-PRF-680 Type II or III Solvent, degreasing

Local Purchase Aqueous cleaning products

Local Purchase Mask material

Local Purchase Plastic media (MIL-P-85891 Type II) (maximum

media hardness of 3.5 MOH)
or
Walnut hull (A-A-1722 Type II) (grain-soft
abrasive walnut hulls, Grade 20/30)
or
Sodium Bicarbonate

Local Purchase Paint remover (SAE-AMS-1375)

Local Purchase Steel grit

(3) Referenced information

REFERENCE DESCRIPTION

SPECIAL TOOLS, FIXTURES, To get sources of materials and to get

EQUIPMENT, AND CONSUMABLES recommended concentrations and temperatures
section of aqueous cleaners

MIL-STD-1504 To get the procedure for abrasive blast paint

removal

C. Job Set-up

Not applicable

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

D. Procedure

Subtask 32-41-87-100-001-A01

(1) Clean carbon disks (necessary before you install the disks again)

CAUTION: USE ONLY ISOPROPYL ALCOHOL TO CLEAN CARBON PARTS. OTHER

CLEANING MATERIALS CAN CAUSE CHANGES IN BRAKE
PERFORMANCE AND CAN INCREASE THE OXIDATION RATE. OTHER
CLEANING MATERIALS CAN CAUSE CARBON PARTS TO BREAK.

(a) Surface contamination

1 Use a vacuum cleaner and a plastic-bristle brush to remove loose

contamination on the end plate assemblies, rotor assemblies, and stator
assemblies.

You can remove loose contamination with compressed air, but it puts
carbon particles in the air. These particles can cause damage to
electrical circuits of adjacent electrical equipment.

2 Soak a cloth with isopropyl alcohol and use the cloth to remove grease, oil, or
hydraulic fluid. Use clean, dry, compressed air to dry the disk.

(b) Absorbed contamination

CAUTION: CLEAN THE CARBON PARTS BY PROCEDURES THAT LET THE

PARTS BE IDENTIFIED AGAIN AFTER THE PROCEDURE. THIS
CLEANING PROCEDURE CAN REMOVE IDENTIFICATION MARKS
ON THE CARBON PARTS.

1 Remove contamination on the disks (refer to paragraph 1.D.(1)(a).

CAUTION: PUT SPACERS BELOW EACH DISK IN AN OVEN. CONTAMINATION

IS NOT REMOVED FROM DISKS WITHOUT SPACERS.

2 Put the carbon disks in an oven with graphite spacers or ceramic spacers
below the bottom disk and between the disks. Increase the oven temperature
to 260° - 315 °C (500° - 600 °F). Remove the disks after 2 hours in the oven
and let them air cool.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-100-002-A01

(2) Clean Non-metal Parts

WARNING: BEFORE YOU USE BUTYL ALCOHOL, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE ALCOHOL. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER,
THE MATERIAL SAFETY DATA SHEET (MSDS), AND GOVERNMENT
REGULATIONS. BUTYL ALCOHOL MAY CAUSE INJURY TO YOU OR
MAKE YOU SICK WHEN SAFETY INSTRUCTIONS ARE NOT OBEYED. AN
MSDS GIVES INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP,
AND DISCARD BUTYL ALCOHOL. GET INSTRUCTIONS FROM YOUR
EMPLOYER ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD
BUTYL ALCOHOL.

CAUTION: USE ONLY THE CLEANING FLUIDS AND SOLVENTS GIVEN IN THIS
PARAGRAPH TO CLEAN RUBBER SEALS AND O-RINGS. FLUIDS THAT
ARE NOT APPROVED CAN CAUSE DAMAGE TO RUBBER PARTS.

CAUTION: APPLY CLEANING PRODUCTS FOR ONLY THE TIME THAT IS

NECESSARY TO SUFFICIENTLY CLEAN THE PARTS. CONTACT OF PARTS
AND CLEANING PRODUCTS FOR A LONG TIME CAN CAUSE DAMAGE TO
SOME PARTS.

(a) Clean non-metallic parts with butyl alcohol or aqueous cleaning products.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-100-003-A01

(3) Clean metal parts (Refer to IPL Figure 2)

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

CAUTION: MAKE SURE THAT CONTAMINATION IS FULLY REMOVED FROM THE

BOLTS AND NUTS. CONTAMINATION CAN PREVENT FULL INSPECTION
OF THE BOLTS AND NUTS. CONTAMINATION CAN CAUSE INCORRECT
BOLT TENSION WHEN THE BOLTS OR NUTS ARE TORQUED.

CAUTION: DO NOT USE A WIRE BRUSH TO CLEAN ALUMINUM PARTS. DO NOT USE
SAND IN THE ABRASIVE-BLAST PROCEDURE TO CLEAN ALUMINUM
PARTS. A WIRE BRUSH OR SAND CAUSE DAMAGE TO THE ANODIZE
LAYER ON ALUMINUM PARTS.

CAUTION: DO NOT USE ALKALINE CLEANING SOLVENTS TO CLEAN ALUMINUM

PARTS. THESE SOLVENTS CAN CAUSE DAMAGE TO THESE PARTS.

CAUTION: CAREFULLY OBEY THE MANUFACTURER’S INSTRUCTIONS FOR USE OF

AQUEOUS CLEANING PRODUCTS. INCORRECT PROCEDURES CAN
CAUSE DAMAGE TO PARTS OR UNSATISFACTORY CLEANING.

(a) Clean metal parts with MIL-PRF-680 Type II or III solvent or aqueous cleaning
products. You can use the specified solvent to clean pistons (2-115) and
sleeves (2-50) with backup rings (2-5, 2-70) that are not removed. You can use the
aqueous cleaning products to clean sleeves (2-50) with scraper rings (2-55) and
O-rings (2-60) that are not removed. Make sure that all bolt and nut threads are fully
clean. Some of these parts can be cadmium plated (refer to the ILLUSTRATED
PARTS LIST to identify these parts).

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-120-001-A01

(4) Remove paint from the piston housing by abrasive blast

NOTE: Refer to paragraph 1.D.(5) for a procedure to remove paint with a chemical.
(Ref.: Subtask 32-41-87-110-001-A01)

WARNING: OBEY GOVERNMENT REGULATIONS AND INSTRUCTIONS FROM YOUR

EMPLOYER WHEN YOU TOUCH, KEEP, AND DISCARD PAINT THAT IS
REMOVED. THE PAINT THAT IS REMOVED IS POSSIBLY DANGEROUS
TO THE SKIN, EYES, AND LUNGS.

(a) Apply mask material to threaded ports and adjuster cavities.

(b) Blast the parts by the procedures in MIL-STD-1504. Use media that does not cause
damage to the anodize layer. Refer to examples that follow:

1 Plastic media (MIL-P-85891 Type II) (maximum media hardness of 3.5 MOH).

2 Walnut hulls (A-A-1722 Type II) (grain-soft abrasive walnut hulls, Grade 20/30).

3 Sodium Bicarbonate

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-110-001-A01

(5) Remove paint from the piston housing with a chemical

NOTE: Refer to paragraph 1.D.(4) for a procedure to remove paint by abrasive blast.
(Ref.: Subtask 32-41-87-120-001-A01)

WARNING: BEFORE YOU USE PAINT REMOVER, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE PAINT REMOVER. THESE
INSTRUCTIONS INCLUDE INSTRUCTIONS FROM THE MANUFACTURER,
THE MATERIAL SAFETY DATA SHEET (MSDS), AND GOVERNMENT
REGULATIONS. PAINT REMOVER MAY CAUSE INJURY TO YOU OR
MAKE YOU SICK WHEN SAFETY INSTRUCTIONS ARE NOT OBEYED. AN
MSDS GIVES INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP,
AND DISCARD PAINT REMOVER. GET INSTRUCTIONS FROM YOUR
EMPLOYER ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD
PAINT REMOVER.

WARNING: OBEY GOVERNMENT REGULATIONS AND INSTRUCTIONS FROM YOUR

EMPLOYER WHEN YOU TOUCH, KEEP, AND DISCARD THE PAINT THAT
IS REMOVED. THE PAINT THAT IS REMOVED IS POSSIBLY DANGEROUS
TO THE SKIN, EYES, AND LUNGS.

(a) Apply mask material to threaded ports and adjuster cavities.

(b) Apply paint remover (SAE-AMS-1375) that can remove urethane paint and epoxy
primer and does not cause damage to aluminum or steel parts. Refer to instructions
from the manufacturer of the paint remover.

(c) Remove the paint remover.

Subtask 32-41-87-120-002-A01

(6) Remove paint or corrosion from the torque tube and the back plate assembly by abrasive
blast

(a) Put mask plugs in threaded holes.

(b) Lightly abrasive blast the part with glass beads or 40 - 80 mesh abrasive media (for
example: steel grit, steel shot, sand, or aluminum oxide). Use dry, compressed air to
remove the dust from the part.

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

INSPECTION/CHECK

TASK 32-41-87-200-801-A01
1. General Inspection / Check

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

(1) Tools, fixtures, and equipment

NOTE: Refer to the SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLES

section for the sources of materials.

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE MIN. QTY. DESCRIPTION

ASTM E1417 Type I, 1 Penetrant inspection equipment
Method A, Level 2
ASTM E1444 1 Magnetic particle inspection equipment
Local Purchase As Necessary Measurement tools (accurate to 0,02 mm
(0.001 inch))
Local Purchase 1 Spring tester (136 kg (300 pound) min. capacity)
Local Purchase As Necessary Magnifiers (for visual inspections)
Local Purchase As Necessary Bright lights (for visual inspections)
Local Purchase 1 Megohmmeter to measure between 10 and
110 megohms under 45 to 50 VDC
Local Purchase As Necessary Digital thermometer (precision ± 0,05 °C
(± 0.09 °F))
Local Purchase 1 Digital voltmeter (precision ± 0.02 mV)
Local Purchase 1 Electronic ice point (type K with a compensation
accuracy of ± 0,5 °C (± 0.9 °F) from 15 to 35°C
(59 to 95 °F) ambient temperature)
Local Purchase 1 Temperature controlled furnace
Local Purchase 1 Thermocouple extension wire (type K)
Local Purchase 1 Ground continuity tester (THOMSON double
bridge with a range of 100 microhms to 11
ohms)

(2) Consumables

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE DESCRIPTION
ASTM E1417 Type I, Method A, Level 2 Penetrant inspection fluid
ASTM E1444 Magnetic particle inspection

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

(3) Referenced information

Not applicable

C. Job Set-up

Not applicable

D. Procedure

Subtask 32-41-87-200-001-A01

(1) Inspection Intervals (Refer to IPL Figure 1 and IPL Figure 2)

(a) Do inspections at the intervals that are shown below or do the inspections more
frequently. Do all inspections on a brake assembly that caused a thermal relief plug (in
the wheel) to release tire pressure.

(b) Refer to all pages in this INSPECTION / CHECK section for full inspection procedure
data.

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

INSPECTION AT INSPECTIONS AT
PART
INSPECTION TYPE EACH HEAT OTHER INTERVALS
DESCRIPTION
SINK CHANGE
Clip and Rivets on Carbon Disks (Refer to NOTE 2)
Torque Tube (1-160) X
Back Plate Assembly (1-75) X
Thrust Plate Assembly (1-125) X
Piston Housing (1-220) X
All Parts of Adjuster Assemblies (1-170) X
Heat Shield Assembly (1-100) X
Temperature Sensor (1-65) X
VISUAL Bolts (1-20, 1-70) X
Bleeder Valves (1-175) X
Hydraulic Fittings (1-190) X
Screws (1-35, 1-155), Washers X
(1-10, 1-45, 1-150), and Nuts (1-5, 1-40,
1-145)
Pistons (2-115) X
Piston Sleeves (2-50) X
Springs (2-110) (load capacity) X
MEASUREMENT Torque Tube (1-160) X
Temperature Sensor (1-65) (Refer to NOTE 3)
Drive Slots in Carbon Disks (Refer to NOTE 2)
Torque Tube (1-160) (Refer to NOTE 1)
Piston Housing (1-220) (Refer to NOTE 1)
Back Plate Assembly (1-75) (Refer to NOTE 1)
NDT
(Non-Destructive Thrust Plate Assembly (1-125) X
Test) Bolts (1-20, 1-70) X
Adjuster Pins (2-40) X

NOTE: 1) Do this inspection at each 3rd heat sink change.

NOTE: 2) Do these inspections if the heat sink is not fully worn and is installed again.

NOTE:. 3) Do these inspections only if the brake shows signs of overheat or if the
temperature sensor is returned for defective or unusual indications.

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PART No. 2-1684

Subtask 32-41-87-200-002-A01

(2) Carbon parts inspection (When the heat sink is not fully worn and is installed again)

(a) Heat sink return rules

1 When a heat sink is fully worn, or has damage that is more than maximum
limits, send the heat sink to Goodrich (refer to the DISASSEMBLY section).
(Ref.: Subtask 32-41-87-030-002-A01)

(b) Visual inspections of carbon

1 Do a visual inspection of the carbon material in each part for cracks. A crack
that is longer than 1,6 mm (1/16 inch) and starts from the outer or inner edge is
not permitted. A crack that starts from a drive slot or that goes through the full
thickness of the part is not permitted.

2 Do a visual inspection of the wear surfaces for damage. Surface damage that
has a depth more than 1,6 mm (1/16 inch) is not permitted. Surface damage
that has a total area of more than 64,5 cm² (one inch²) is not permitted.

(c) Dimension inspection of drive slots

1 Measure the dimensions of the drive slots in the end plate assemblies and the
stator assemblies. Refer to Figure 5001 or the FITS AND CLEARANCES
section for dimension limits (Ref.: Subtask 32-41-87-820-001-A01). A drive slot
that is worn to more than the limit is not permitted.

END PLATE
ASSEMBLY
OR
STATOR
ASSEMBLY

21,08 (0.830)
MAXIMUM
RIVETS CLIP
RIVETS
CLIPS

ROTOR ASSEMBLY

Drive Slot Inspection (When the heat sink is not fully worn and is installed again)
Figure 5001 /GRAPHIC 32-41-87-992-501-A01

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PART No. 2-1684

(d) Hardness inspection of carbon

1 Do an inspection of the hardness of the carbon material. A carbon part with an

outer edge or inner edge that easily breaks into small pieces is not permitted.

(e) Visual inspection of clips

1 Do a visual inspection of the metal clips on each disk. A damaged clip is not
permitted. A clip with a crack is not permitted.

(f) Visual inspection of rivets

CAUTION: DO NOT PEEN A LOOSE RIVET. A LOOSE RIVET THAT IS PEENED

CAN BREAK.

1 Do a visual inspection for damaged rivets and for loose rivets. A damaged rivet
or a loose rivet is not permitted.

(g) Check for loose rotor clips.

1 Move the two clips on each lug together as shown in Figure 5002.

2 Measure the gap between the two clips.

3 Hold one clip in place and move the opposite clip away.

4 Measure the gap.

5 Move the two clips together again.

6 Hold the other clip in place and move the opposite clip away.

7 Measure the gap.

8 Reject the heat sink if the difference of the gap in step 4 minus the gap in
step 2 is more than 0,89 mm (0.035 inch).

Reject the heat sink if the difference of the gap in step 7 minus the gap in
step 2 is more than 0,89 mm (0.035 inch).

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RIVETS GAP
CLIPS

ROTOR
ASSEMBLY

Permitted Movement of Rotor Clips

Figure 5002 /GRAPHIC 32-41-87-991-502-A01

(h) Visual Inspection for catalytic oxidation

NOTE: Soft or missing carbon is an indication of catalytic oxidation. Brown or orange

stains are initial indications of possible catalytic oxidation. Catalytic oxidation
is most common on the outer diameter of carbon disks and on the non-wear
surfaces of the thrust plate and end plate. This oxidation can occur on the
inner diameter of carbon disks.

1 Do a visual inspection of all surfaces of each carbon disk when a heat sink is
removed or a reason other than wear (refer to Figures 5003 and 5004). Lightly
scratch carbon surfaces with a fingernail or a sharp plastic pick to find soft,
oxidized carbon. If you find a heat sink with catalytic oxidation or with brown or
orange stains, contact Goodrich Corporation to find out the procedure to return
the heat sink.

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PART No. 2-1684

THICKNESS
LOSS IN
LOCAL AREAS

Catalytic Oxidation and Local Damage on a Thrust Plate

Figure 5003 /GRAPHIC 32-41-87-991-503-A01

Catalytic Oxidation and Local Damage on the Outer Diameter of a Stator

Figure 5004 /GRAPHIC 32-41-87-991-504-A01

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PART No. 2-1684

Subtask 32-41-87-200-003-A01

(3) Torque Tube (1-160) Inspection (Refer to IPL Figure 1)

(a) Visual inspection of the torque lugs

1 Do a visual inspection of the torque lugs for damage (refer to Figure 5005). The
side surfaces must be smooth to let the end plate assemblies and stator
assemblies move easily. Polished side surfaces of the torque lugs are
permitted. Repair damaged areas. Refer to the REPAIR section
(Ref.: Subtask 32-41-87-300-003-A01). Reject a torque tube with damage that
is more than a limit.

(b) Dimension inspection of the torque lugs

1 If you see wear or corrosion in an area on a torque lug, measure the width of
the lug in that area. Refer to Figure 5005 or the FITS AND CLEARANCES
section for dimension limits (Ref.: Subtask 32-41-87-820-001-A01). Reject a
torque tube with a lug that has a width that is less than the limit.

(c) Visual inspection of the torque tube

1 Do a visual inspection of the torque tube for cracks. Local repair of surface
cracks on the torque tube to 0,51 mm (0.020 inch) maximum depth is
permitted. Refer to the REPAIR section (Ref.: Subtask 32-41-87-300-003-A01).
Reject a torque tube with a crack that has more depth than the limit.

(d) Non-Destructive Test (NDT) inspection of the torque tube

WARNING: BEFORE YOU USE MAGNETIC PARTICLE (ASTM E1444) OR

PENETRANT FLUIDS (ASTM E1417 TYPE I, METHOD A, LEVEL 2),
READ, UNDERSTAND, AND OBEY ALL SAFETY INSTRUCTIONS
FOR THESE FLUIDS. THESE INSTRUCTIONS INCLUDE
INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT
REGULATIONS. THIS FLUID MAY CAUSE INJURY TO YOU OR
MAKE YOU SICK WHEN SAFETY INSTRUCTIONS ARE NOT
OBEYED. AN MSDS GIVES INSTRUCTIONS ON HOW YOU MUST
SAFELY USE, KEEP, AND DISCARD THESE FLUIDS. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON HOW YOU MUST
SAFELY USE, KEEP, AND DISCARD THESE FLUIDS.

1 At specified intervals, do a penetrant inspection (ASTM E1417 Type I,

Method A, Level 2) or magnetic particle inspection (ASTM E1444). Local repair
of surface cracks on the torque tube to 0,51 mm (0.020 inch) maximum depth is
permitted. Refer to the REPAIR section (Ref.: Subtask 32-41-87-300-003-A01).
Reject a torque tube with a crack that has more depth than the limit.

(e) Visual inspection of threaded holes in the torque tube

1 Do a visual inspection of the threaded holes at the end of the torque tube.
Repair small damage to the threads with a 0.375-24 UNJF-3B tap. More thread
repair is possible with a Heli-Coil® insert. Refer to the REPAIR section
(Ref.: Subtask 32-41-87-300-003-A01). Reject a torque tube with a hole that
cannot be repaired with a Heli-Coil® insert.

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PART No. 2-1684

19,30 - 20,00
(0.760 - 0.787)
AND 25,40 (1,000) MAX. LENGTH
0,30 (0.012) AND 1,14 (0.045) MAX.
MAXIMUM VARIATION DEPTH ON THE TOP
FROM LUG TO LUG SURFACE
TORQUE TUBE

TORQUE LUG

0.375-24 UNJF-3B
TO 24,89 (0.984) DEPTH

Torque Lug Inspection

Figure 5005 /GRAPHIC 32-41-87-991-505-A01

(f) Visual inspection of stud holes in the torque tube

1 If you remove a stud (1-50), do a visual inspection of the hole for the stud.
Reject a torque tube with a hole that has damage that will not give a press fit of
the stud.

(g) Hardness inspection of the torque tube

1 Measure the hardness of a torque tube from an overheated brake assembly.

Refer to paragraph 1.D.(17) (Ref.: Subtask 32-41-87-200-017-A01).

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PART No. 2-1684

Subtask 32-41-87-200-004-A01

(4) Piston housing (1-220) inspection (Refer to IPL Figure 1)

(a) Do a visual inspection of the piston housing for surface damage and cracks. Local
repair is permitted as follows:

1 Damage on a static seal surface

a Repair of this damage to 0,02 mm (0.001 inch) maximum depth is

permitted if the diameter does not increase to more than the limit. Refer
to the REPAIR section (Ref.: Subtask 32-41-87-300-004-A01). Refer to
Figure 5006 or the FITS AND CLEARANCES section for dimension
limits (Ref.: Subtask 32-41-87-820-001-A01). Reject a piston housing
that has a seal surface that has damage to more than the limit.

2 Damage that is not on a static seal surface

a Local repair of this damage to 0,51 mm (0.020 inch) maximum depth is

permitted. Refer to the REPAIR section
(Ref.: Subtask 32-41-87-300-004-A01). Reject a piston housing that has
damage to more than the limit.

PISTON HOUSING STATIC SEAL

SURFACE

50,88
(2.003)
MAX. DIA.

Inspection of the Static Seal Surface

Figure 5006 /GRAPHIC 32-41-87-991-506-A01

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PART No. 2-1684

(b) Non-Destructive Test (NDT) inspections of the piston housing

NOTE: Remove paint on the piston housing assembly before penetrant inspection.
Refer to the CLEANING section) (Ref.: Subtask 32-41-87-120-001-A01 or
Subtask 32-41-87-110-001-A01).

WARNING: BEFORE YOU USE PENETRANT FLUID (ASTM E1417 TYPE I,

METHOD A, LEVEL 2), READ, UNDERSTAND, AND OBEY ALL
SAFETY INSTRUCTIONS FOR THE FLUID. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE
MATERIAL SAFETY DATA SHEET (MSDS), AND GOVERNMENT
REGULATIONS. THIS FLUID MAY CAUSE INJURY TO YOU OR
MAKE YOU SICK WHEN YOU DO NOT OBEY SAFETY
INSTRUCTIONS. THE MSDS TELLS HOW YOU MUST SAFELY USE,
KEEP, AND DISCARD THIS FLUID. GET INSTRUCTIONS FROM
YOUR EMPLOYER THAT TELL HOW YOU MUST SAFELY USE,
KEEP, AND DISCARD THIS FLUID.

1 At specified intervals, do a penetrant inspection (ASTM E1417 Type I,

Method A, Level 2) of the full piston housing. Reject a piston housing with a
crack that has more depth than the limit for surface repair.

(c) Visual inspection of Lee plugs

1 Do a visual inspection of each Lee plug for leakage. Refer to Figure 5007.
Replace a Lee plug that leaks. Refer to the REPAIR section
(Ref.: Subtask 32-41-87-300-004-A01).

MOUNTING
FLANGE

LEE PLUGS (1-215)

(16 LOCATIONS ON THE
PISTON HOUSING)

Locations of Mounting Flange and Lee Plugs

Figure 5007 /GRAPHIC 32-41-87-991-507-A01

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(d) Visual inspection of ports

1 Do a visual inspection of the inlet ports and the bleeder ports. Repair damaged
threads (refer to the REPAIR section). Repair a damaged seal surface of an
inlet port. Refer to the REPAIR section (Ref.: Subtask 32-41-87-300-004-A01).
Reject a piston housing with a seal surface that you cannot repair.

(e) Hardness inspection of the piston housing

1 If the brake assembly was overheated, measure the hardness or conductivity

of the area that touches the torque tube. Refer to paragraph 1.D.(17)
(Ref.: Subtask 32-41-87-200-017-A01).

Subtask 32-41-87-200-005-A01

(5) Thrust plate assembly (1-125) inspection (Refer to IPL Figure 1)

(a) Visual inspection of the thrust plate assembly

1 Do a visual inspection of the thrust plate assembly for damage and for cracks.
Do an inspection for cracks from the stress-relief hole in each expansion slot
(refer to Figure 5008). Repair these cracks. Refer to the REPAIR section
(Ref.: Subtask 32-41-87-300-005-A01). Discard a thrust plate (1-140) with a
crack that is more than 2,54 mm (0.100 inch) long. Reject a thrust plate with
damage that prevents correct operation of the part.

(b) Non-Destructive Test (NDT) inspection of the thrust plate

WARNING: BEFORE YOU USE PENETRANT FLUID (ASTM E1417 TYPE I,

1 At specified intervals, do an penetrant inspection (ASTM E1417 Type I,

Method A, Level 2) for cracks. Do this inspection around the stressrelief hole in
each expansion slot (refer to Figure 5008). Repair these cracks. Refer to the
REPAIR section (Ref.: Subtask 32-41-87-300-005-A01). Discard a thrust plate
(1-140) with a crack that is more than 2,54 mm (0.100 inch) long.

(c) Part replacement on the thrust plate assembly

1 Do a visual inspection of the insulators (1-130) and retaining rings (1-135) for
cracks or other damage. Replace damaged parts. Refer to the REPAIR section
(Ref.: Subtask 32-41-87-300-005-A01).

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PART No. 2-1684

EXPANSION STRESS-RELIEF
SLOT HOLES

PENETRANT
INSPECTION
AREAS

Inspection of a Thrust Plate Assembly

Figure 5008 /GRAPHIC 32-41-87-991-508-A01

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Subtask 32-41-87-200-006-A01

(6) Back plate assembly (1-75) inspection (Refer to IPL Figure 1)

(a) Visual inspection of the back plate assembly

1 Do a visual inspection of the back plate assembly for surface damage and for
cracks. Surface damage that prevents correct operation of the part is not
permitted. Local repair of surface cracks to 0,51 mm (0.020 inch) maximum
depth is permitted. Rrefer to the REPAIR section
(Ref.: Subtask 32-41-87-300-006-A01). Discard a back plate (1-95) that has
damage to more than a limit.

(b) Non-Destructive Test (NDT) inspection of the back plate assembly

WARNING: BEFORE YOU USE MAGNETIC PARTICLE (ASTM E1444) OR

1 At specified intervals, do a penetrant inspection (ASTM E1417 Type I,

Method A, Level 2) or magnetic particle inspection (ASTM E1444). The
removal of backplate pads (1-90) is not necessary for the inspection. Local
repair of surface cracks to 0,51 mm (0.020 inch) maximum depth is permitted.
Refer to the REPAIR section (Ref.: Subtask 32-41-87-300-006-A01). Discard a
back plate (1-95) that has damage to more than a limit.

(c) Part replacement on the back plate assembly

CAUTION: DO NOT PEEN A LOOSE RIVET. A LOOSE RIVET THAT IS PEENED

CAN BREAK.

1 Replace damaged back plate pads (1-90), loose rivets (1-80), or damaged
washers (1-85). Refer to the REPAIR section.
(Ref.: Subtask 32-41-87-300-006-A01)

NOTE: A loose rivet is permitted if the rivet head is the correct shape.

(d) Hardness inspection of the back plate

1 Measure the hardness of a back plate from an overheated brake assembly

(refer to paragraph 1.D.(17)). (Ref.: Subtask 32-41-87-200-017-A01)

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PART No. 2-1684

Subtask 32-41-87-200-007-A01

(7) Piston (2-115) inspection (Refer to IPL Figure 2)

(a) Visual inspection of the pistons

1 Do a visual inspection of each piston for surface damage. Small surface

scratches that you cannot feel with a fingernail are permitted on the seal
surface. Repair a seal surface with scratches that you can feel with a fingernail.
Refer to the REPAIR section (Ref.: Subtask 32-41-87-300-007-A01). Discard a
piston with damage that you cannot repair.

(b) Dimension inspections of the pistons

1 If you see wear on an outer surface, measure the diameter. Refer to

Figure 5009 or the FITS AND CLEARANCES section for dimension limits.
Repair a surface with wear that is not more than the limits. Refer to the REPAIR
section (Ref.: Subtask 32-41-87-300-007-A01). Discard a piston with damage
that is more than a limit (Ref.: Subtask 32-41-87-820-001-A01).

SEAL SURFACE

33,15 (1.305) 40,26 (1.585)

MIN. DIA. MIN. DIA.

Piston Inspection
Figure 5009 /GRAPHIC 32-41-87-991-509-A01

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Subtask 32-41-87-200-008-A01

(8) Sleeve (2-50) inspection (Refer to IPL Figure 2)

(a) Visual inspection of the sleeves

1 Do a visual inspection of each sleeve for surface damage. Small surface

scratches that you cannot feel with a fingernail are permitted on the seal
surface of the bore. Repair a bore with scratches that you can feel with a
fingernail. Refer to the REPAIR section (Ref.: Subtask 32-41-87-300-008-A01).
Discard a sleeve with damage that you cannot repair.

(b) Dimension inspections of the sleeves

1 If you see wear on one or two inner wear surfaces, measure the diameter.
Refer to Figure 5010 or the FITS AND CLEARANCES section for dimension
limits (Ref.: Subtask 32-41-87-820-001-A01). Repair a bore with wear that is
more than the limits. Refer to the REPAIR section
(Ref.: Subtask 32-41-87-300-008-A01). Discard a sleeve with damage that is
more than a limit.

Sleeve Inspection
Figure 5010 /GRAPHIC 32-41-87-991-510-A01

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Subtask 32-41-87-200-009-A01

(9) Bushing (2-95) inspection (Refer to IPL Figure 2)

(a) Dimension inspection of the bushings

1 Measure each bushing for wear. Refer to Figure 5011 or the FITS AND
CLEARANCES section for dimension limits
(Ref.: Subtask 32-41-87-820-001-A01). Discard a bushing that is worn to more
than a limit.

Inspection of Bushings
Figure 5011 /GRAPHIC 32-41-87-991-511-A01

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Subtask 32-41-87-200-010-A01

(10) Spring (2-110) Inspection (Refer to IPL Figure 2)

(a) Strength inspection of the springs

1 Put a 54,5 mm (2.15 inch) calibration rod below the ram of the spring test
machine (refer to Figure 5012). Set the dial indicator to zero. Remove the
calibration rod.

WARNING: DO NOT DO THE TEST WITHOUT A PROTECTIVE SHIELD AROUND

THE SPRING TEST MACHINE. A SPRING THAT IS NOT IN THE
CORRECT POSITION CAN EJECT FROM THE TEST MACHINE
WITH MUCH FORCE.

2 Put the spring below the ram at the center of the ram.

3 Compress the spring with the ram until the dial indicator shows zero. A
minimum of 113 Kg (250 pounds) is necessary to compress a satisfactory
spring to the 54,5 mm (2.15 inch) height. Discard a defective spring.

RAM

DIAL INDICATOR
54,5 (2.15)

CALIBRATION SPRING
ROD

PLATFORM

Adjuster Spring Inspection

Figure 5012 /GRAPHIC 32-41-87-991-512-A01

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Subtask 32-41-87-200-011-A01

(11) Adjuster pin (2-40) inspection (Refer to IPL Figure 2)

(a) Visual inspection of the adjuster pins

1 Do a visual inspection of each adjuster pin for damage. Chrome plating on the
shaft is permitted to extend in an irregular pattern into the shaded area (refer to
Figure 5013). Small surface scratches that you cannot feel with a fingernail are
permitted on the shaft. Reject a pin with a scratch that you can feel on the shaft
with a fingernail.

(b) Non-Destructive Test (NDT) inspection of the adjuster pins

1 Do a magnetic particle inspection (ASTM E1444) for cracks. Discard a pin with
a crack.

Inspection of Adjuster Pins

Figure 5013 /GRAPHIC 32-41-87-991-513-A01

Subtask 32-41-87-200-012-A01

(12) Ball (2-30) Inspection (Refer to IPL Figure 2)

(a) Visual inspection of the balls

1 Do a visual inspection of each ball for scored, galled, or corroded areas. Small
scored areas are permitted. Discard a galled or corroded ball.

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Subtask 32-41-87-200-013-A01

(13) Heat Shield Assembly (1-100) Inspection (Refer to IPL Figure 1)

(a) Visual inspection of the heat shield

1 Do a visual inspection of the heat shield for separation of the inner and outer
layers. Weld repair a heat shield with layers that are broken apart. Refer to the
REPAIR section (Ref.: Subtask 32-41-87-300-009-A01). Reject a heat shield
with damage that you cannot repair.

2 Do a visual inspection of the heat shield for cracks. Repair cracks that start at
the end of the heat shield and are not more than 12,7 mm (0.50 inch) long.
Refer to the REPAIR section (Ref.: Subtask 32-41-87-300-009-A01). Reject a
heat shield with a crack in some other location or with a crack that is longer
than the limit.

Subtask 32-41-87-200-014-A01

(14) Temperature Sensor (1-65) Inspection (Refer to IPL Figure 1)

(a) Visual inspection of the temperature sensor

1 Do a visual inspection of the probe and the connector pins for damage (refer to
Figure 5014). Straighten a pin or a probe with a small bend. Discard the sensor
if the probe has a crack or a connector pin is damaged.

X1 X2
(CONNECTOR) (HOUSING ASSEMBLY)

PIN C

PROBE

PIN B
PIN A SENSOR BODY

Temperature Sensor
Figure 5014 /GRAPHIC 32-41-87-991-514-A01

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PART No. 2-1684

(b) Measurement inspection of the temperature sensor (1-65)

Do the functional tests that follow on a temperature sensor from a brake that has signs
of overheat or gives defective or unusual indications.

1 Do all tests as explained below under normal standard test laboratory ambient
conditions:

– Ambient temperature: between 15 and 30 °C (59 and 86 °F)

– Ambient barometric pressure: 840 to 1070 mbar (12.2 to 15.5 psi)

– Relative humidity: less than 90%

2 Operational test

a Connect the Chromel extension wire to the pin "C" of the connector of
the temperature sensor.

b Connect the Alumel extension wire to the pin "A" of the connector of the
temperature sensor.

c Connect the positive (+) lead of the electronic ice point to the Chromel
extension wire.

d Connect the negative (-) lead of the electronic ice point to the Alumel
extension wire.

e Connect the electronic ice point to the digital voltmeter.

f Install the end of the probe of the temperature sensor (between 20 and
30 mm (0.8 and 1.2 in)) into boiling water.

g Measure the temperature of the boiling water with a digital thermometer.

h Make sure that the voltage increases and stabilizes at a value which
complies with the measured temperature as written in the following
table:

TEMPERATURE VOLTAGE

101 °C (213.8 °F) 4.08 to 4.20 mV

100 °C (212 °F) 4.04 to 4.16 mV

99 °C (210.2 °F) 4.00 to 4.12 mV

98 °C (208.4 °F) 3.95 to 4.07 mV

97 °C (206.6 °F) 3.91 to 4.03 mV

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PART No. 2-1684

3 Ground continuity test

a Connect the ground continuity tester to the temperature sensor.

b Make sure that the ground continuity resistance, between the points Xl
and X2, is less than or equal to 20 milliohms.

4 Insulation test at ambient temperature

a Connect all the pins of the connector together.

b Apply a voltage of between 45 and 50 VDC with the megohmmeter

between the pins and the housing assembly of the temperature sensor.

c Make sure that the insulation resistance is more than 100 megohms.

5 Insulation test at 600 °C (1112 °F)

WARNING: BEFORE YOU CONTINUE WITH THE TEST, PUT ON

THERMAL PROTECTIVE GLOVES AND EYE PROTECTION.
THE TEMPERATURE SENSOR CAN GET VERY HOT AND
CAUSE YOU INJURY.

a Connect all the pins of the connector together.

b Put the end of the probe (between 20 and 30 mm (0.8 and 1.2 in)) of the
temperature sensor into the temperature controlled furnace.

c Increase the temperature of the temperature controlled furnace to

between 580 and 620 °C (1076 and 1148 °F).

NOTE: The heat may cause the colour of the end of the probe of the
temperature sensor to change, this is normal.

d Apply a voltage of between 45 and 50 VDC with the megohmmeter

between the pins and the housing assembly of the temperature sensor.

e Make sure that the insulation resistance is more than or equal to 20

megohms.

32-41-87
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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-200-015-A01

(15) Bolt (1-20, 1-70) inspection (Refer to IPL Figure 1)

(a) Visual Inspection of the bolts

1 Do an inspection for corrosion, cracks, and damage in the threads or on the

radius below the bolt head. Discard a defective bolt.

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

(b) Non-Destructive Test (NDT) inspection of the bolts

WARNING: BEFORE YOU USE MAGNETIC PARTICLE (ASTM E1444) OR

1 At specified intervals, do a penetrant inspection (ASTM E1417 Type I,

Method A, Level 2), magnetic particle (ASTM 1444) or ultrasonic inspection on
the bolts (1-20). Discard bolts that show a crack indication. The bolts can be
cadmium plated.

2 At specified intervals, do a penetrant inspection (ASTM E1417 Type I,

Method A, Level 2), ultrasonic inspection or eddy current inspection of the
bolts (1-70). Discard a defective bolt.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-200-016-A01

(16) Screw (1-35, 1-155), washer (1-10, 1-45, 1-150), and nut (1-5, 1-40, 1-145) inspection (Refer
to IPL Figure 1)

(a) Visual inspection of the screws, washers, and nuts

1 Do a visual inspection of the screws, washers, and nuts for damage and for
cracks. Damage that prevents correct operation of the part is not permitted.
Some of these parts can be cadmium plated (refer to the ILLUSTRATED
PARTS LIST to identify these parts). Discard defective parts.

Subtask 32-41-87-200-017-A01

(17) Special inspection procedures for an overheated brake assembly (Refer to IPL Figure 1)

(a) Hardness inspection of the torque tube (1-160)

1 Measure the hardness in four locations on the top torque lug as shown in
Figure 5015. Discard the torque tube if the average of all hardness values is
less than 285 BHN (with a 10 mm ball and 3000 kg load) or Rc30 (with a brale
indentor).

(b) Hardness inspection of the back plate (1-95)

1 Measure the hardness on the torque tube contact area of the back plate as
shown in Figure 5015. Discard the back plate if the average of all hardness
values is less than 285 BHN (with a 10 mm ball and 3000 kg load) or Rc30
(with a brale indentor).

(c) Hardness inspection of the piston housing (1-220)

1 Measure the hardness or eddy current conductivity in four locations minimum

on the torque tube contact area of the piston housing.

a Measure the conductivity or hardness on the torque tube contact area in

the areas shown in Figure 5015.

b If the conductivity is 43.0% IACS or less, the piston housing has

sufficient hardness for use. If the conductivity is more than 43.0% IACS,
measure the hardness.

c Remove the anodize layer in the test areas before measuring hardness.
If the hardness of the piston housing is less than 130 BHN, Rb 75, or
equivalent, discard the piston housing.

(d) Do the inspections given in the "Measurement inspection of the temperature sensor"
in this CHECK section.

32-41-87
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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Hardness Measurement Locations on Parts from an Overheated Brake

Figure 5015 /GRAPHIC 32-41-87-991-515-A01

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INTENTIONALLY BLANK
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

REPAIR

TASK 32-41-87-300-801-A01
1. Repair

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

(1) Tools, fixtures, and equipment

NOTE: Refer to the SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLES

section for the sources of materials.

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE MIN. QTY. DESCRIPTION

(2) Consumables

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE DESCRIPTION
ASTM E1417 Type I, Method A, Level 2 Penetrant inspection fluid
ASTM E1444 Magnetic particle inspection fluid
As Necessary Abrasive paper, 320 grit and 400 grit
MIL-PRF-680 Type II or III Solvent, degreasing
SAE-AMS-1640 Chemical that removes corrosion
MIL-C-5541 Class 1A Conversion coat
As Necessary Paint materials (paint, primers, thinner)

(3) Referenced information

Not applicable

C. Job Set-up

Not applicable

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

D. Procedure

Subtask 32-41-87-300-001-A01

(1) General Surface Repair Descriptions

CAUTION: DO NOT MAKE A SUDDEN CHANGE IN THE CONTOUR IN REPAIRED

AREAS. DO NOT MAKE A ROUGH SURFACE IN REPAIRED AREAS. A
CRACK CAN START AT A DAMAGED AREA THAT YOU DO NOT REPAIR
OR THAT YOU DO NOT REPAIR CORRECTLY.

(a) General Description of a Blend Repair

1 A "blend repair" gradually changes the contour from the repaired surface to the
adjacent initial surfaces. A blend repair removes a minimum quantity of metal
and makes a smooth surface (without tool marks or scratches). Use #400 grit
abrasive paper to remove scratches that are made by initial blend tools or
large-grit abrasive paper.

(b) Description of a "50-to-1" Blend Repair

1 A "50-to-1" diameter for each blend repair is recommended for the flat areas
where a circular repair pattern is possible. A "50-to-1" blend repair is not
possible for areas that are not flat. Calculate a "50-to-1" diameter as follows:

a Measure the depth "d" of the damaged area. If the depth is more than
the permitted limit, reject the part.

b Multiply "d" by 50 to get the recommended diameter "D" of the repaired

area (refer to Figure 6001).

CALCULATION FOR THE

DIAMETER OF A CIRCULAR
REPAIR PATTERN DIAMETER "D"
OF THE REPAIRED AREA
"D" = 50 x "d" DAMAGED
AREA

BLEND
DEPTH "d"
CONTOUR
OF DAMAGE
The Recommended Diameter of Blend-Repaired Areas
Figure 6001 /GRAPHIC 32-41-87-991-601-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-300-002-A01

(2) Heat sink (1-105) replacement (Refer to IPL Figure 1)

(a) When a heat sink is fully worn or is damaged to more than maximum limits, send the
full heat sink to Goodrich. Refer to the DISASSEMBLY section for the shipping
procedure. (Ref.: Subtask 32-41-87-030-002-A01)

Subtask 32-41-87-300-003-A01

(3) Torque tube (1-160) repair (Refer to IPL Figure 1)

(a) Surface Damage repair of the torque tube (refer to Figure 6002):

1 Locally blend surface damage and cracks on the torque tube between torque
lugs to 0,51 mm (0.020 inch) maximum depth.

WARNING: BEFORE YOU USE MAGNETIC PARTICLE (ASTM E1444) OR

2 Do a magnetic particle inspection (ASTM E1444) or penetrant inspection

(ASTM E1417 Type I, Method A, Level 2) of repaired areas for cracks. If you
find a crack after repair to the maximum depth, reject the part.

3 Polish the rough side surfaces of the torque lugs, but do not decrease the width
of a lug to less than the limit.

4 Locally blend a damaged top surface of a torque lug to not more than the limits.
Remove burrs, radius sharp edges, and polish the repaired area.

5 Apply paint to repaired areas (refer to "Apply Paint to the Torque Tube").

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

(b) Torque Tube (1-160) Threaded Hole Repair

1 Repair small damaged areas of threads with a 0.375-24 UNJF-3B tap to a

24,89 mm (0.984 inch) tap depth (refer to Figure 6002).

2 Repair large damaged areas of threads with a Heli-Coil® insert as follows:

a Drill the hole to 9,92 mm (25/64 inch) diameter and to a maximum depth
of 30,50 mm (1.201 inch).

b Tap the hole with a Heli-Coil® tap, P/N 6FPB, to a minimum full thread
depth of 24,89 mm (0.984 inch).

7,24 - 8,25 HELI-COIL

(0.285 - 0.325)

HOLE REPAIR
R
WITH A HELI-COIL
25,40 (1.000) MAX. LENGTH
1,14 (0.045) MAX. DEPTH
ON THE TOP SURFACE
19,30 - 20,00
(0.760 - 0.787) 0,89 - 1,09
AND (0.035 - 0.043)
0
0,30 (0.012) X 45 CHAMFER
MAXIMUM
VARIATION
FROM LUG TO TORQUE LUG
LUG

0.375-24 UNJF-3B
X 24,89 (0.984) DEPTH
TORQUE TUBE

Repair of Torque Lugs

Figure 6002 /GRAPHIC 32-41-87-991-602-A01

c Install a Heli-Coil® insert, P/N 1191-6CN0938, with a Heli-Coil® tool,

P/N 7552-6, until the top coil is 7,24 - 8,25 mm (0.285 - 0.325 inch) from
the end of the torque lug (refer to Figure 6002). Break off the insert tang
with a Heli-Coil® tool, P/N 3692-6.

d Hammer stamp a single zero (0) adjacent to the repaired hole.

32-41-87 Page 6004

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GOODRICH CORPORATION, A PART OF COLLINS AEROSPACE
COMPONENT MAINTENANCE MANUAL
Part Number 2-1684

TEMPORARY REVISION NO. 32-4

Page Affected: 6004

Changes: Revise paragraph D.(3)(b)2c as follows:

(b) Torque Tube (1-160) Threaded Hole Repair

1 Repair small damaged areas of threads with a 0.375-24 UNJF-3B tap to a 24,89 mm (0.984 inch)
tap depth (refer to Figure 6002).

2 Repair large damaged areas of threads with a Heli-Coil® insert as follows:

a Drill the hole to 9,92 mm (25/64 inch) diameter and to a maximum depth of 30,50 mm
(1.201 inch).

b Tap the hole with a Heli-Coil® tap, P/N 6FPB, to a minimum full thread depth of 24,89 mm
(0.984 inch).

7,24 - 8,25 HELI-COIL®

(0.285 - 0.325)

HOLE REPAIR
WITH A HELI-COIL®
25,40 (1.000) MAX. LENGTH
1,14 (0.045) MAX. DEPTH
ON THE TOP SURFACE
19,30 - 20,00
(0.760 - 0.787)
AND
0,30 (0.012)
MAXIMUM 0,89 - 1,09
VARIATION (0.035 - 0.043)
FROM LUG X 45° CHAMFER
TO LUG
TORQUE LUG
0.375-24 UNJF-3B
X 24,89 (0.984) DEPTH
TORQUE TUBE
NOTE: DIMENSIONS SHOWN ARE IN MM (INCHES).

Repair of Torque Lugs

Figure 6002 / GRAPHIC 32-41-87-991-602-A01

c Install a Heli-Coil® insert, P/N 1191-6CN0562, with a Heli-Coil® insert tool, P/N 7552-6, until
the top coil is 7,24 to 8,25 mm (0.285 to 0.325 inch) from the end of the torque lug (refer
to Figure 6002). Break off the insert tang with a Heli-Coil® tool, P/N 3692-6.

d Hammer stamp a single zero (0) adjacent to the repaired hole.

U.S. Export Classification: EAR 9E991 32-41-87

COLLINS AEROSPACE PROPRIETARY Page 2 of 2
Subject to the restriction on the cover page. Feb 22/22
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

(c) Apply paint to the torque tube (1-160)

WARNING: BEFORE YOU USE MIL-PRF-680 TYPE II OR III SOLVENT,

ISOPROPYL ALCOHOL, BUTYL ALCOHOL, OR THINNER
(MIL-T-81772), READ, UNDERSTAND, AND OBEY ALL SAFETY
INSTRUCTIONS FOR THESE SOLVENTS. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE
MATERIAL SAFETY DATA SHEET (MSDS), AND GOVERNMENT
REGULATIONS. THESE SOLVENTS MAY CAUSE INJURY TO YOU
OR MAKE YOU SICK WHEN YOU DO NOT OBEY SAFETY
INSTRUCTIONS. THE MSDS TELLS HOW YOU MUST SAFELY USE,
KEEP, AND DISCARD THESE SOLVENTS. GET INSTRUCTIONS
FROM YOUR EMPLOYER THAT TELL HOW YOU MUST SAFELY
USE, KEEP, AND DISCARD THESE SOLVENTS.

1 Soak a cloth with MIL-PRF-680 Type II or III solvent and use the cloth to clean
the torque tube.

2 Apply mask material to threaded holes and to the end surface that touches the
back plate assembly (1-75).

CAUTION: WEAR CLEAN FABRIC GLOVES TO TOUCH CLEANED TORQUE

TUBES. PAINT WILL POSSIBLY NOT BOND TO A TORQUE TUBE
THAT IS TOUCHED WITH BARE HANDS.

3 Lightly abrasive blast the torque tube with 40 - 80 mesh abrasive media (for
example: steel grit, steel shot, sand, or aluminum oxide). Steel grit abrasive is
recommended. Use clean, dry compressed air to remove dust from the part.

4 Soak a cloth with paint thinner (MIL-T-81772) and use the cloth to clean the
torque tube.

5 Apply two layers of an aluminum-color, high-temperature paint to the torque

tube. Apply the paint in two hours or less after the abrasive blast procedure. Let
the paint air dry.

NOTE: "VHT", "Heat-Rem", or Federal Specification TT-P-28 are examples of

this type of paint.

6 Remove the mask materials.

7 Heat the torque tube to cure the paint (refer to instructions from the paint
manufacturer). Do not heat the torque tube to more than 204 °C (400 °F).

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-300-004-A01

(4) Piston housing assembly (1-205) repair (Refer to IPL Figure 1)

WARNING: BEFORE YOU USE CONVERSION COAT (MIL-C-5541, CLASS 1A), READ,
UNDERSTAND, AND OBEY ALL SAFETY INSTRUCTIONS FOR THE
CONVERSION COAT. THESE INCLUDE MANUFACTURER'S
INSTRUCTIONS, THE MATERIAL SAFETY DATA SHEET (MSDS), AND
GOVERNMENT REGULATIONS. CONVERSION COAT MAY CAUSE
INJURY TO YOU OR MAKE YOU SICK WHEN SAFETY INSTRUCTIONS
ARE NOT OBEYED. AN MSDS GIVES INSTRUCTIONS ON HOW TO
SAFELY USE, KEEP, AND DISCARD CONVERSION COAT. GET
INSTRUCTIONS FROM YOUR EMPLOYER ON HOW TO SAFELY USE,
KEEP, AND DISCARD CONVERSION COAT.

(a) Surface damage repair

1 Use #320 grit (or finer) abrasive cloth to locally blend damaged areas to the
maximum depths as follows (refer to Figure 6003):

a Damage on a static seal surface - Do a local blend or overall repair of

this damage to 0,02 mm (0.001 inch) maximum depth. Reject the piston
housing if the diameter becomes more than the limit.

b Damage that is not on a static seal surface - Locally blend to remove

damage to 0,51 mm (0.020 inch) maximum depth.

2 Apply conversion coat (MIL-C-5541 Class 1A) to the repaired areas. Let the
conversion coat dry.

3 Apply primer and paint to the repaired areas (refer to "Apply Paint to the Piston
Housing").

(b) Damaged port repair

1 Repair small areas of damage to the threads of the inlet ports with a
0.5625-18 UNJF-3B tap (refer to Figure 6003).

2 Repair damage to the seal surface of an inlet port as follows:

a Machine the seal surface to SAE-AS5202-06 dimensions. Machine to

not more than 0,25 mm (0.010 inch) depth from the initial location of the
seal surface.

b Apply conversion coat (MIL-C-5541 Class 1A) to the repaired areas. Let
the conversion coat dry.

3 Repair small areas of damage to threads of the bleeder ports with a

0.500-20 UNJF-3B tap (refer to Figure 6003).

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

STATIC SEAL
SURFACE

50,88
(2.003)
MAX. DIA.

Static Seal Surfaces and Port Locations in a Piston Housing

Figure 6003 /GRAPHIC 32-41-87-991-603-A01

4 Bleeder Port - Repair with a Plug

a Machine the port to 14,81 - 15,32 mm (0.583 - 0.603 inch) diameter and
14,23 -14,73 mm (0.560 - 0.580 inch) depth. Ream to 16,08 - 16,28 mm
(0.633 - 0.641 inch) diameter and 14,23 - 14,73 mm (0.560 - 0.580 inch)
depth.

b Use a bottoming tap to make 0.6875-20 UN-3B perfect threads in the

port to a 13,72 mm (0.540 inch) minimum depth.

c Make a plug as shown in Figure 6004.

d Clean the plug and the port with MIL-PRF-680 Type II or III solvent and
permit the parts to fully dry.

e Apply epoxy adhesive, 3M™ No. 2216 B/A Gray Scotch-Weld™ to the
threads of the plug. Install the plug only until the plug touches the bottom
of the port (do not tighten). Let the adhesive dry. Refer to instructions on
the container label to mix, apply, and dry the adhesive.

f Machine the plug flush with the surface of the piston housing.

g Machine and thread the plug as shown in Figure 6005.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

h Apply conversion coat (MIL-C-5541 Class 1A) to the top of the plug and
to other bare aluminum in the repaired area. Do not touch the repaired
area until it is fully dry.

i Fully assemble the brake assembly and do a "High-Pressure Leak Test"

(refer to the TESTING AND FAULT ISOLATION section for the test.
Ref.: Subtask 32-41-87-700-002-A01. Do an inspection for hydraulic
fluid leakage from the repaired area. Reject the piston housing if you see
leakage.

0.6875-20 UN-3A THREADS 15,62 - 16,13

FULL LENGTH (0.615 - 0.635)
1,27 - 1,78
(0.050 - 0.070) 2,29 - 2,79
MATERIAL: (0.090 - 0.110)
2014-T6
0
2014-T651 118
2024-T86
2024-T81 DRILL HOLE FULL LENGTH
2024-T851 TO 2,92 - 3,43
ALUMINUM (0.115 - 0.135) DIA.
ALLOY

Repair Plug for the Bleeder Port

Figure 6004 /GRAPHIC 32-41-87-991-604-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

CDRILL TO 12,80 - 13,00 (0.504 - 0.512) DIA.

AND TO 1,50 - 1,80 (0.059 - 0.071) DEPTH.
TAP DRILL TO 14,00 - 14,50 (0.551 - 0.571) DEPTH
AND TAP 0.500-20 UNJF-3B FULL THREADS
PER SAE-AS8879
TO 9,75 - 10,26 (0.384 - 0.404) DEPTH.

0
100
0
80
0,13 - 0,25
(0.005 - 0.010)
0
X 45 CHAMFER

Port Configuration in the Repair Plug

Figure 6005 /GRAPHIC 32-41-87-991-605-A01

(c) Replacement of Lee Plugs (1-215) in the piston housing

CAUTION: REMOVE LEE PLUGS BY A PROCEDURE THAT DOES NOT

DAMAGE THE REAMED HOLE, OR THE 45° ANGLED SEAT.

1 Drill and tap a hole in the pin. Install the Lee pin removal tool or a
locally-manufactured equivalent tool in the pin. Slide the striker against the bolt
head to remove the pin (refer to Figure 6006).

2 Drill and tap the Lee plug. Install the Lee plug removal tool or a
locally-manufactured equivalent tool in the plug. Slide the striker against the
bolt head to remove the plug (refer to Figure 6006).

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PART No. 2-1684

PIN REMOVAL PIN STRIKER

PISTON HOUSING PIN REMOVAL TOOL

ASSEMBLY

PLUG REMOVAL STRIKER

PLUG

PISTON HOUSING PLUG REMOVAL TOOL

ASSEMBLY

Lee Plug Removal

Figure 6006 /GRAPHIC 32-41-87-991-606-A01

3 Measure the diameter of the hole in the piston housing. If the hole diameter is
5,555 - 5,618 mm (0.2187 - 0.2212 inch), and the hole has a good finish (63 Ra
or better), install a standard size Lee plug (P/N PLGA2180010) as follows:

a Push the Lee plug into the hole until the plug firmly touches the shoulder
in the hole.

b Start the small end of the pin into the tapered hole in the Lee plug. Make
sure that the pin goes in straight.

c Hit the end of the pin 2 or 3 times with a hammer and flat punch to align
the pin with the end of the plug ± 0,13 mm (± 0.005 inch). The outer
diameter of the punch must be smaller than the outer diameter of the
pin.

d After the brake is fully assembled, do a high pressure leak test (refer to
the TESTING AND FAULT ISOLATION section).
(Ref.: Subtask 32-41-87-700-002-A01).

4 If the hole is larger than the specified size, or has a surface finish that is
rougher than 63 Ra, install an oversize Lee plug as follows:

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

WARNING: BEFORE YOU USE CONVERSION COAT (MIL-C-5541,

CLASS 1A), READ, UNDERSTAND, AND OBEY ALL SAFETY
INSTRUCTIONS FOR THE CONVERSION COAT. THESE
INCLUDE MANUFACTURER'S INSTRUCTIONS, THE
MATERIAL SAFETY DATA SHEET (MSDS), AND
GOVERNMENT REGULATIONS. CONVERSION COAT MAY
CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN
SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS
GIVES INSTRUCTIONS ON HOW TO SAFELY USE, KEEP,
AND DISCARD CONVERSION COAT. GET INSTRUCTIONS
FROM YOUR EMPLOYER ON HOW TO SAFELY USE, KEEP,
AND DISCARD CONVERSION COAT.

a Ream the hole to a 5,809 - 5,872 mm (0.2287 - 0.2312 inch) diameter

and to a 63 Ra (or better) surface finish.

b Clean the hole (refer to the CLEANING section).

(Ref.: Subtask 32-41-87-100-003-A01)

c Apply conversion coat (MIL-C-5541 Class 1A) to the hole and let it dry.

CAUTION: DO NOT REMOVE THE LAYER OF WAX ON THE LEE PLUG. A

LEE PLUG IS MORE DIFFICULT TO INSTALL IF THE WAX IS
REMOVED.

d Push an oversize Lee plug, P/N PLGA2280010, into the hole until the
plug firmly touches the shoulder in the hole.

e Start the small end of the pin into the tapered hole in the Lee plug. Make
sure that the pin goes in straight.

f Hit the end of the pin 2 or 3 times with a hammer and flat punch to align
the pin with the end of the plug ± 0,13 mm (± 0.005 inch). The outer
diameter of the punch must be smaller than the outer diameter of the
pin.

g After you assemble the brake, do a high-pressure leak test (refer to the
TESTING AND FAULT ISOLATION section).
(Ref.: Subtask 32-41-87-700-002-A01).

5 If the hole has damage that prevents correct installation of an oversize Lee
plug, P/N PLGA2280010, install a larger plug, P/N PLGA2500010, as follows:

a Ream the hole to a 6,350 - 6,414 mm (0.2500 - 0.2525 inch) diameter

and to a 63 Ra (or better) surface finish.

b Clean the hole (refer to the CLEANING section).

(Ref.: Subtask 32-41-87-100-003-A01)

c Apply conversion coat (MIL-C-5541 Class 1A) to the hole. Let the
conversion coat dry.

d Push an oversize Lee plug (P/N PLGA2500010) into the hole until the
plug firmly touches the shoulder in the hole.

e Start the small end of the pin into the tapered hole in the Lee plug. Make
sure that the pin goes in straight.

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PART No. 2-1684

g After you assemble the brake, do a high-pressure leak test (refer to the
TESTING AND FAULT ISOLATION section).
(Ref.: Subtask 32-41-87-700-002-A01)

(d) Lockwire hole repair

WARNING: BEFORE YOU USE CONVERSION COAT (MIL-C-5541, CLASS 1A),

READ, UNDERSTAND, AND OBEY ALL SAFETY INSTRUCTIONS
FOR THE CONVERSION COAT. THESE INCLUDE
MANUFACTURER'S INSTRUCTIONS, THE MATERIAL SAFETY
DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CONVERSION COAT MAY CAUSE INJURY TO YOU OR MAKE YOU
SICK WHEN SAFETY INSTRUCTIONS ARE NOT OBEYED. AN
MSDS GIVES INSTRUCTIONS ON HOW TO SAFELY USE, KEEP,
AND DISCARD CONVERSION COAT. GET INSTRUCTIONS FROM
YOUR EMPLOYER ON HOW TO SAFELY USE, KEEP, AND
DISCARD CONVERSION COAT.

1 Drill through a clogged lockwire hole to open the hole. Use a 1,58 mm
(0.062 inch) drill bit.

2 If the lockwire hole has too much damage, drill a new hole adjacent to the
damaged hole at approximately a 45° angle. Use a 1,58 mm (0.062 inch)
diameter drill bit.

3 Clean the hole (refer to the CLEANING section).

(Ref.: Subtask 32-41-87-100-003-A01)

4 Apply conversion coat (MIL-C-5541 Class 1A), primer, and paint to a repaired
lockwire hole or a new lockwire hole. Let the conversion coat dry. Refer to
"Apply Paint to the Piston Housing".

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PART No. 2-1684

(e) Apply paint to the piston housing (1-220)

NOTE: Refer to the CLEANING section for paint removal instructions.

(Ref.: Subtask 32-41-87-120-001-A01 or Subtask 32-41-87-110-001-A01)

WARNING: DO NOT DISCARD WASTE FROM WATER-BORNE PAINT IN THE

SAME WASTE CONTAINER AS WASTE FROM SOLVENT-BORNE
PAINTS THAT CONTAIN ALUMINUM POWDER (SUCH AS
METALLIC PAINT). DISCARD THESE DIFFERENT TYPES OF
WASTE PRODUCTS IN SEPARATE, FIRE-PROOF CONTAINERS.
WHEN WATER TOUCHES ALUMINUM POWDER (WHICH MAKES
HYDROGEN GAS), A FIRE OR EXPLOSION IS POSSIBLE.

WARNING: BEFORE YOU USE CONVERSION COAT (MIL-C-5541, CLASS 1A),

READ, UNDERSTAND, AND OBEY ALL SAFETY INSTRUCTIONS
FOR THE CONVERSION COAT. THESE INCLUDE
MANUFACTURER’S INSTRUCTIONS, THE MATERIAL SAFETY
DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
CONVERSION COAT MAY CAUSE INJURY TO YOU OR MAKE YOU
SICK WHEN SAFETY INSTRUCTIONS ARE NOT OBEYED. AN
MSDS GIVES INSTRUCTIONS ON HOW TO SAFELY USE, KEEP,
AND DISCARD CONVERSION COAT. GET INSTRUCTIONS FROM
YOUR EMPLOYER ON HOW TO SAFELY USE, KEEP, AND
DISCARD CONVERSION COAT.

1 Use thinner to clean the piston housing.

2 Apply mask material for primer as shown in Figure 6007.

3 Apply one layer of primer. Refer to the instructions from the manufacturer.

4 Apply mask material for paint as shown in Figure 6007.

5 Apply two layers of paint. Refer to the instructions from the manufacturer.

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NP
2 LOCATIONS

PO
PM
3 LOCATIONS

PO PRIMER ONLY

NP NO PRIMER OR URETHANE PAINT

PM THE MASK DIAMETER ON THE WASHER SEAT

FOR URETHANE PAINT IS 13,72 - 14,48 (0.540 - 0.570).
APPLY PRIMER AND URETHANE PAINT TO SURFACES THAT HAVE NO LIMITS

Mask and Paint Limits for the Piston Housing

Figure 6007 /GRAPHIC 32-41-87-991-607-A01

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Subtask 32-41-87-300-005-A01

(5) Thrust plate assembly (1-125) repair (Refer to IPL Figure 1)

(a) Repair cracks that start in the stress-relief hole at the end of an expansion slot as
follows (refer to Figure 6008):

1 Machine the hole to a maximum diameter of 10,08 mm (0.397 inch). Discard

the thrust plate if the crack is not removed.

2 Break sharp edges on the machined hole.

Expansion Slot Repair Limits on Thrust Plate Assembly

Figure 6008 /GRAPHIC 32-41-87-991-608-A01

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(b) Part replacement procedure

1 Replace a cracked insulator (1-130) or damaged retaining ring (1-135) (refer to

Figure 6009).

WEAR PIN
MOUNTING STUDS
(REF.) THRUST PLATE
ASSEMBLY (1-125)

RETAINING
RING (1-135)
INSULATOR (1-130)

Installation of an Insulator
Figure 6009 /GRAPHIC 32-41-87-991-609-A01

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Subtask 32-41-87-300-006-A01

(6) Back plate assembly (1-75) repair (Refer to IPL Figure 1)

(a) Surface Damage Repair

WARNING: BEFORE YOU USE MAGNETIC PARTICLE (ASTM E1444) OR

1 Locally blend surface damage and cracks to 0,51 mm (0.020 inch) maximum
depth. Do a magnetic particle inspection (ASTM E1444) or penetrant
inspection (ASTM E1417 Type I, Method A, Level 2) of repaired areas for
cracks. Discard the back plate (1-95) if cracks are not removed.

2 Clean the back plate assembly (refer to the CLEANING section).

CAUTION: WEAR CLEAN FABRIC GLOVES TO TOUCH CLEANED BACK

PLATES. PAINT WILL POSSIBLY NOT BOND TO A BACK PLATE
THAT IS TOUCHED WITH BARE HANDS.

3 Lightly abrasive blast the back plate assembly with 40 - 80 mesh abrasive
media such as steel grit, steel shot, sand, or aluminum oxide. Steel grit
abrasive is recommended. Use clean, dry compressed air to remove dust from
the part.

4 Soak a cloth with paint thinner (MIL-T-81772) and use the cloth to clean the
back plate assembly.

5 Apply mask material to the surface of each back plate pad (1-90) that touches
the carbon heat sink.

6 Apply mask material to the end surface of the back plate that touches the
torque tube.

7 Apply two layers of an aluminum-color, high-temperature paint (TT-P-28) to the

back plate. Apply the paint in two hours or less after it was abrasive blasted. Let
the paint air dry.

8 Remove the mask materials.

9 Heat the back plate assembly to cure the paint (refer to instructions from the
paint manufacturer). Do not heat the assembly to more than 204 °C (400 °F).

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(b) Back plate pad (1-90) replacement

1 Drill out the rivet (1-80) or grind off the rivet head above the washer (1-85).

2 Attach a new back plate pad. Upset the rivet head until the washer is held
tightly against the back plate pad.

NOTE: Use a radial riveter and the peen and anvil (refer to the SPECIAL
TOOLS, FIXTURES, AND EQUIPMENT AND CONSUMABLES
section).

Subtask 32-41-87-300-007-A01

(7) Piston (2-115) repair (Refer to IPL Figure 2)

(a) Polish the surfaces with #320 (or finer) grit abrasive cloth to remove small damage
(nicks, scratches, etc.). Polish to the limits and surface finish as shown in Figure 6010.

Piston Repair Limits

Figure 6010 /GRAPHIC 32-41-87-991-610-A01

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Subtask 32-41-87-300-008-A01

(8) Sleeve (2-50) Repair (Refer to IPL Figure 2)

(a) Polish outer surfaces with #320 (or finer) grit abrasive cloth to remove small damage
(nicks, scratches, etc.) to a 0,38 mm (0.015 inch) maximum depth.

(b) Apply conversion coat (MIL-C-5541 Class 1A) to the repaired areas. Let the
conversion coat dry.

1 Machine the surface to 38,74 mm (1.525 inches) diameter.

2 Plate hard chrome (QQ-C-320, Class 2, type II) on the machined surface.

3 Machine the surface to the specified size and surface finish (refer to
Figure 6011).

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PART No. 2-1684

Sleeve Repair Limits

Figure 6011 /GRAPHIC 32-41-87-991-611-A01

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PART No. 2-1684

Subtask 32-41-87-300-009-A01

(9) Heat shield (1-100) repair (Refer to IPL Figure 1)

(a) Spot weld at twelve equally-spaced locations around the circumference to connect
layers that are broken apart (refer to Figure 6012).

(b) TIG weld repair with AMS 5680 filler rod is permitted for not more than two cracks at
each end of a heat shield. Repair is permitted only for cracks that start at the end of
the heat shield and are not more than 12,7 mm (0.50 inch) long.

Heat Shield Repair

Figure 6012 /GRAPHIC 32-41-87-991-612-A01

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PART No. 2-1684

Subtask 32-41-87-300-010-A01

(10) Temperature sensor (1-65) repair (Refer to IPL Figure 1)

(a) Bend a bent pin or a bent probe to make a straight pin or probe (refer to Figure 6013).
Reject the sensor if a repaired pin or probe has a crack or a wrinkle. Test the
temperature sensor after repair (refer to the INSPECTION/CHECK section).
(Ref.: Subtask 32-41-87-200-014-A01)

PIN C

PROBE

PIN B
PIN A SENSOR BODY

Temperature Sensor Repair

Figure 6013 /GRAPHIC 32-41-87-991-613-A01

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PART No. 2-1684

ASSEMBLY

TASK 32-41-87-400-801-A01
1. Assembly

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

(1) Tools, fixtures, and equipment

NOTE: Refer to the SPECIAL TOOLS, FIXTURES, EQUIPMENT, AND CONSUMABLES

section for full data on special tools.

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

REFERENCE MIN. QTY. DESCRIPTION

Local Purchase 1 Torque wrench, 1 to 65 Nm (1 to 550
pound-inches) (4% maximum permitted error)
Local Purchase 1 Automatic wrenching machine (4% maximum
permitted error) (optional)
114-291 1 Adjuster assembly/disassembly tool (special tool)
114-293 1 Backup ring installation tool (special tool)
114-1159 1 Backup ring sizing tool (special tool)
114-325 1 Piston installation support tool (special tool)
114-326 1 Piston installation bullet tool (special tool)
114-327 1 Piston installation guide tool (special tool)
114-245 1 Adjuster pin installation tool (special tool)
114-239 1 Radial riveting peen (special tool)
114-241 1 Radial riveting anvil (special tool)

(2) Consumables

NOTE: Equivalent alternatives are permitted for the assembly fluid (MCS-352) and for the
sealer in the list that follows. Equivalent alternatives are not permitted for anti-seize
compound and hydraulic fluid.

REFERENCE DESCRIPTION
SAE-AMS-2518 or MIL-PRF-83483 or Fel-Pro C5A Anti-seize compound
NSA 307-110 Hydraulic fluid
MCS-352 Assembly fluid, (Optional)
683-3-2 Sealant, base material
X-310-A Sealant, catalyst
UniFlor®, P/N NYE8512S Assembly Lubricant (Recommended)

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(3) Referenced information

Not applicable

C. Job Set-up

Not applicable

D. Procedure (Refer to IPL Figure 1 and IPL Figure 2)

Subtask 32-41-87-400-001-A01

(1) Replacement rules for O-rings, backup rings, scraper rings, and bushings

(a) Install new O-rings (1-165, 1-185, 1-195, 2-65, 2-85) and
backup rings (2-90) at each heat sink change. Replace scraper rings (2-55), backup
rings (2-5, 2-70), or bushings (2-95) only if they are damaged. Install a new
O-ring (2-60) only if the scraper ring (2-55) in the same adjuster assembly is
discarded.

Subtask 32-41-87-400-002-A01

(2) Lubricant application

WARNING: BEFORE YOU USE HYDRAULIC FLUID, READ, UNDERSTAND, AND OBEY
ALL SAFETY INSTRUCTIONS FOR THE FLUID. THESE INSTRUCTIONS
INCLUDE INSTRUCTIONS FROM THE MANUFACTURER, THE MATERIAL
SAFETY DATA SHEET (MSDS), AND GOVERNMENT REGULATIONS.
HYDRAULIC FLUID MAY CAUSE INJURY TO YOU OR MAKE YOU SICK
WHEN SAFETY INSTRUCTIONS ARE NOT OBEYED. AN MSDS GIVES
INSTRUCTIONS ON HOW YOU MUST SAFELY USE, KEEP, AND DISCARD
HYDRAULIC FLUID. GET INSTRUCTIONS FROM YOUR EMPLOYER ON
HOW YOU MUST SAFELY USE, KEEP, AND DISCARD HYDRAULIC FLUID.

CAUTION: REMOVE HYDRAULIC FLUID THAT FALLS ON BRAKE PARTS (REFER TO

THE CLEANING SECTION). HYDRAULIC FLUID CAN CAUSE DAMAGE TO
PAINTED SURFACES AND CAN CAUSE COLLECTION OF
CONTAMINATION.

CAUTION: APPLY MCS-352 LUBRICANT AND HYDRAULIC FLUID IMMEDIATELY

BEFORE ASSEMBLY OF PARTS. AIR INCREASES THE VISCOSITY OF
MCS-352 LUBRICANT, WHICH CAN CAUSE POSSIBLE DAMAGE TO
PARTS DURING ASSEMBLY PROCEDURES.

(a) Apply lubricant to O-rings and other parts at the specified times. The correct lubricant
is UniFlor® assembly lubricant, phosphate-ester hydraulic fluid
(NSA 307-110) or a mixture of hydraulic fluid and MCS-352 lubricant. Only a thin layer
of UniFlor® assembly lubricant is necessary on the O-rings.

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Subtask 32-41-87-440-001-A01

(3) Adjuster assembly (1-170) (Refer to IPL Figure 1 and IPL Figure 2)

WARNING: INSTALL PARTS WITH CORRECT TOOLS AND PROCEDURES.

INCORRECT TOOLS AND PROCEDURES CAN CAUSE AN ADJUSTER
SPRING AND OTHER PARTS TO EJECT AT HIGH SPEED.

(a) Refer to Figure 7001 to see an assembled adjuster assembly.

O-RING

O-RING (2-60)
O-RING
(2-65)

O-RING
(2-85)

Parts of an Adjuster Assembly

Figure 7001 /GRAPHIC 32-41-87-991-701-A01

(b) Put the spring (2-110), and the spring guide (2-105) into the piston (2-115). Put the
retaining ring (2-100) on top of the spring guide. If one outer edge of the retaining ring
has an outer edge that is not sharp, put this edge against the spring guide.

(c) Put the assembly tool in the drill press or arbor press and put the piston (2-115) on the
press table as shown in Figure 7002.

(d) Push the assembly tool down until the spring guide is below the lower groove of the
piston. Refer to Figure 7002. Do not install the retaining ring in the top groove. Lock
the press. Install the retaining ring and make sure that the ring is fully into the bottom
groove. Unlock the press and slowly release pressure on the assembly tool.

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Installation of a Spring in a Piston

Figure 7002 /GRAPHIC 32-41-87-991-702-A01

(e) Install the O-ring (2-60) and the scraper (excluder) ring (2-55) into the groove of the
sleeve (2-50) as follows:

1 Put the O-ring into the groove of the scraper ring (refer to Figure 7003).

2 Bend the scraper ring sufficiently to let you install the ring, but do not make a
bend that causes damage to the ring.

NOTE: If necessary, use a heat gun or hot water to make the scraper ring soft
before the ring is installed.

3 Install the scraper ring assembly in the groove of the sleeve. Slide a finger
around the full length of the scraper ring to push it fully into the groove.

4 Push the piston-installation "bullet" tool (Figure 9005) through the sleeve. The
tool makes sure that the scraper ring is fully into the groove.

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O-RING
(2-60)

Assembly and Installation of the Scraper Ring Assembly

Figure 7003 /GRAPHIC 32-41-87-991-703-A01

(f) Apply a thin layer of lubricant to a new O-ring (2-85).

NOTE: An optional O-ring (2-85B) is recommended for operations with a history of

brakes with leakage or drag. This O-ring is made from a different material and
is identified by a green dot. You can identify the the O-ring used from the
information in the table below.

Item Number Part Number Color Code Dot

2-85A 68-1519 Red

2-85B 68-1580 Green

(g) Install a bushing (2-95), two new backup rings (2-90), and the new, lubricated
O-ring (2-85) into the piston as shown in Figure 7004.

(h) Install a seal retainer (2-80) and a retaining ring (2-75) into the groove in the piston.
Put the ends of the retaining ring above the cut-away part of the seal retainer. The
retaining ring can be cadmium plated.

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RETAINING
RING SEAL BUSHING
O-RING
(2-75) RETAINER (2-95)
(2-85)
(2-80)

BACKUP
RINGS
(2-90) PISTON
(2-115)

Installation of Parts into the Piston

Figure 7004 /GRAPHIC 32-41-87-991-704-A01

(i) Install one backup ring (2-70) into the groove on the piston (2-115). Pull the backup
ring against the end of the groove to make the backup ring to be flat again.

NOTE: Install a new backup ring only to replace a damaged backup ring.

(j) Apply a thin layer of lubricant to a new O-ring (2-65). Make sure that the O-ring has a
yellow color-code mark (refer to Figure 7005).

Color-Code Mark on O-rings (1-165, 2-65)

Figure 7005 /GRAPHIC 32-41-87-991-705-A01

(k) Install the new, lubricated O-ring (2-65) into the groove on the piston and behind the
backup ring (2-70) as shown in Figure 7001.

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(l) Apply a thin layer of lubricant to the outer diameter of the O-ring (2-65) and the backup
ring (2-70).

CAUTION: USE THE GUIDE TOOL TO INSTALL THE PISTON INTO THE SLEEVE.
OTHER TOOLS OR PROCEDURES CAN CAUSE DAMAGE TO A O-RING
OR BACKUP RING.

(m) Put the "bullet" tool into the end of the piston (2-115) and the "guide" tool on the end of
the sleeve (2-50) as shown in Figure 7006. Put the piston on the "support" tool and
carefully push the guide tool and sleeve down on the piston and support tool. Remove
the tools.

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O-RING BACKUP RING

(2-65) (2-70)

Installation of the Piston into the Sleeve

Figure 7006 /GRAPHIC 32-41-87-991-706-A01

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(n) Put a pin retainer (2-45) on the end of the sleeve (2-50). Engage the tabs and notches
of the parts. The pin retainer (2-45) can be cadmium plated.

CAUTION: USE THE ADJUSTER PIN INSTALLATION TOOL TO INSTALL THE

ADJUSTER PIN. OTHER TOOLS OR PROCEDURES CAN CAUSE DAMAGE
TO A O-RING OR BACKUP RING.

(o) Put the adjuster pin installation tool onto the end of the adjuster pin (2-40) as shown in
Figure 7007. Apply a thin layer of lubricant to the tool. Carefully push the adjuster pin
and tool through the pin retainer and piston. Make sure that the head of the adjuster
pin installs into the recess of the pin retainer.

(p) Put the assembly on the work table with the pin retainer on the bottom. Remove the
tool.

Installation of the Adjuster Pin (2-40)

Figure 7007 /GRAPHIC 32-41-87-991-707-A01

CAUTION: KEEP THE TORQUE WRENCH PERPENDICULAR (AT A 90° ANGLE) TO

THE ADJUSTER PIN. THE ADJUSTER PIN CAN BREAK IF THE TORQUE
WRENCH IS NOT KEPT PERPENDICULAR TO THE ADJUSTER PIN.

(q) Push the piston (2-115) against the pin retainer (2-45). Install a new adjuster
tube (2-35) into the spring guide (2-105). Install a ball (2-30) and a self-locking
nut (2-25) on the adjuster pin (2-40), with the flat side of the ball against the nut. The
nut (2-25) can be cadmium plated.

Test for the nuts - Use your hand to turn each nut as far as possible on the adjuster
pin. Discard the nut if the adjuster pin extends out of the adjuster pin.

(r) Torque the nut.

(s) Install an instruction plate (2-20) (with lettering visible), a cover (2-15) and a snap ring
(2-10) into the end of the piston. Make sure that the snap ring installs into the top,
inner groove of the piston (refer to Figure 7002). The snap ring can be cadmium
plated.

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Subtask 32-41-87-440-002-A01

(4) Piston housing assembly (1-205) (Refer to IPL Figure 1 and IPL Figure 2)

(a) Replacement of loose or removed identification plates (1-200, 1-210)

CAUTION: LIGHTLY HIT THE STAMPS. YOU CAN CAUSE DAMAGE TO AN

IDENTIFICATION PLATE IF YOU HEAVILY HIT A STAMP.

1 Hammer stamp the new identification plates with data that was recorded from
the used identification plates (or with the data that is stamped on the piston
housing). Put the identification plate on a hard surface and lightly hammer
stamp each character. Do not stamp less than 1/4 inch (6,4 mm) from the edge
of an identification plate.

WARNING: BEFORE YOU USE MIL-PRF-680 TYPE II OR III SOLVENT, READ,

UNDERSTAND, AND OBEY ALL SAFETY INSTRUCTIONS FOR THIS
SOLVENT. THESE INSTRUCTIONS INCLUDE INSTRUCTIONS FROM
THE MANUFACTURER, THE MATERIAL SAFETY DATA SHEET
(MSDS), AND GOVERNMENT REGULATIONS. THIS SOLVENT MAY
CAUSE INJURY TO YOU OR MAKE YOU SICK WHEN YOU DO NOT
OBEY SAFETY INSTRUCTIONS. THE MSDS TELLS HOW YOU
MUST SAFELY USE, KEEP, AND DISCARD THIS SOLVENT. GET
INSTRUCTIONS FROM YOUR EMPLOYER THAT TELL HOW YOU
MUST SAFELY USE, KEEP, AND DISCARD THIS SOLVENT.

2 Use MIL-PRF-680 Type II or III solvent to clean the areas on the piston housing
where you install the identification plates. Clean areas where you can easily
read the identification plates when the brake is installed on the airplane.

CAUTION: DO NOT TOUCH THE ADHESIVE WITH YOUR FINGERS.

CONTAMINATION OF THE ADHESIVE ON AN IDENTIFICATION
PLATE CAN CAUSE IT TO COME OFF THE PISTON HOUSING.

3 Remove the backing paper from each identification plate while you hold the
plate on a flat surface. Hold the identification plate only at the edges and do not
bend the plate.

4 Install each identification plate. Press first at the center of the identification
plate and then press toward the edges. Use heavy force on a hand roller to roll
on the full surface of the identification plate.

NOTE: Replace an identification plate that is wrinkled or creased during

installation.

5 Use a clean cloth that is moist with MIL-PRF-680 Type II or III solvent to clean
the identification plates and adjacent areas.

6 Mix the sealer base material, P/N 683-3-2, and the catalyst, P/N X- 310-A (refer
to instructions from the manufacturer). Apply the mixed sealer on and around
the identification plates. Do not touch the sealer for 4 hours minimum.

7 Use tape to attach some protection material on the identification plates until the
brake is assembled.

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(b) Backup ring installation on the sleeve

1 Put a backup ring installation tool on the sleeve (2-50). Push a backup
ring (2-5) the full length of the tool and into the groove of the sleeve. Refer to
Figure 7008.

NOTE: Install a new backup ring (2-5) only in place of a ring that is damaged.

Installation of a Backup Ring on a Sleeve

Figure 7008 /GRAPHIC 32-41-87-991-708-A01

(c) Sizing procedure for the backup rings (2-5)

NOTE: Backup rings, that are not sized, go back to the correct shape after 24 hours
(at room temperature) after installation on the sleeve.

1 Move the backup ring to the location shown in Figure 7009.

2 Temporarily install a split teflon ring as shown in Figure 7009.

3 Push the sizing tool on the backup ring and keep the tool there for two minutes
minimum.

4 Remove the tool and the teflon ring.

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BACKUP RING
(2-5)

Sizing Backup Rings on the Sleeve

Figure 7009 /GRAPHIC 32-41-87-991-709-A01

(d) O-ring installation on the sleeve

1 Move the backup ring (2-5) away from the threaded end of the sleeve (2-50).
Put the installation tool on the threaded end of the sleeve.

2 Apply a thin layer of lubricant to the tool.

3 Slide a lubricated O-ring (1-165) over the tool and into the groove of the sleeve
where shown in Figure 7001. Make sure that the O-ring has a yellow
color-code mark (refer to Figure 7005).

(e) Adjuster installation in the piston housing

1 Apply a thin layer of lubricant to the O-ring (1-165) and to the piston housing
shoulder where the O-ring will touch.

2 Install an adjuster assembly into each cavity of the piston housing. Torque each
adjuster assembly.

3 Lockwire pairs of adjuster assemblies together as shown in Figure 7010.

32-41-87 Page 7012

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

ADJUSTER
ASSEMBLY (1-170)
14 LOCATIONS LOCKWIRE (1-55)
7 LOCATIONS

PISTON HOUSING
ASSEMBLY (1-205)

Lockwire on Adjuster Assemblies

Figure 7010 /GRAPHIC 32-41-87-991-710-A01

32-41-87 Page 7013

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-440-003-A01

(5) Torque tube assembly (1-160) (Refer to IPL Figure 1)

WARNING DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

WARNING DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

(a) Anti-seize Compound Data

CAUTION KEEP SAE-AMS-2518 ANTI-SEIZE COMPOUND FULLY MIXED. THIS

COMPOUND THAT IS NOT MIXED CAN CAUSE INCORRECT BOLT
TENSION WHICH CAN CAUSE A BOLT TO BREAK.

1 Frequently mix SAE-AMS-2518 anti-seize compound. Fully mix the compound

in new containers that are opened.

(b) Stud (1-50) installation (if studs were removed)

1 Use a press to install each stud into a torque tube (1-160) hole (a
high-interference press fit). Refer to Figure 7011.

CAUTION
. CORRECTLY APPLY ANTI-SEIZE COMPOUND. ANTI-SEIZE
COMPOUND THAT IS NOT APPLIED CORRECTLY CAN CAUSE
INCORRECT BOLT TENSION WHICH CAN CAUSE A BOLT TO
BREAK.

CAUTION APPLY ONLY A SPECIFIED ANTI-SEIZE COMPOUND. A

COMPOUND THAT IS NOT A SPECIFIED COMPOUND CAN CAUSE
INCORRECT BOLT TENSION WHICH CAN CAUSE A BOLT TO
BREAK. A COMPOUND THAT IS MIXED WITH A SOLVENT,
LUBRICANT, OR OTHER COMPOUND CAN CAUSE INCORRECT
BOLT TENSION. INCORRECT TENSION CAN CAUSE A BOLT TO
BREAK.

2 Apply a specified anti-seize compound to the threads of the studs (1-50) and
the nuts (1-40). Also apply the compound to the load surfaces of the
washers (1-45), and nuts as shown in Figure 7011. These studs, washers, and
nuts can be cadmium plated.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

3 Install a washer (1-45) and nut (1-40) on the stud.

Test for the nuts - Use your hand to turn each nut as far as possible on a stud.
Discard the nut if the stud extends out of the nut.

4 Torque each nut.

(c) Bolt (1-20), washer (1-10), and nut (1-5) installation

1 Assemble the bolts (1-20), washers (1-10), and nuts (1-5) in the torque tube
holes (refer to Figure 7011). Tighten the nuts with your fingers. These washers
and nuts can be cadmium plated.

Test for the nuts - Use your hand to turn each nut as far as possible on a bolt.
Discard the nut if the bolt extends out of the nut.

NOTE The nuts (1-5) are torqued when the brake assembly is installed on the
airplane.

2 Apply a specified anti-seize compound to the threads of each screw (1-35) and
nut (1-25) and the bearing faces of the screw, washers (1-30) and nut.

3 Install two screws (1-35), washers (1-30), and nuts (1-25) to attach one bolt
retainer (1-15) on each bolt (1-20) head. These screws, washers, nuts, and bolt
retainer can be cadmium plated.

Test for the nuts - Use your hand to turn each nut as far as possible on a bolt.
Discard the nut if the bolt extends out of the nut.

4 Torque each nut.

WASHER TORQUE
SCREW WASHER TUBE (1-160)
(1-35) STUD (1-50) (1-45)
(1-30)
NUT (1-40)

BOLT RETAINER
(1-15)

SCREW
(1-60)

TEMPERATURE
NUT (1-5) WASHER (1-10) BOLT (1-20) NUT (1-25) SENSOR (1-65)

Torque Tube Assembly

Figure 7011 /GRAPHIC 32-41-87-991-711-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-410-001-A01

(6) Attach the piston housing assembly to the torque tube assembly (Refer to IPL Figure 1)

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST. THESE

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION (OSHA)

HAS AN APPLICABLE DANGER WARNING (29 CFR 1910.1027 (M)(3)(II))
AS FOLLOWS: DANGER: CONTAINS CADMIUM. CANCER HAZARD.
AVOID CREATING DUST. CAN CAUSE LUNG AND KIDNEY DISEASE.

(a) Put the piston housing assembly on the work table with the pistons on the bottom
(refer to Figure 7012).

(b) Put the torque tube assembly into the piston housing assembly with the flange of the
torque tube assembly on the top.

(c) Apply a layer of specified anti-seize compound to the threads of each shoulder
screw (1-155) and nut (1-145) and the bearing faces of the screws, nuts and
washers (1-150).

(d) Slide the piston housing assembly up to the flange on the torque tube and align the
temperature sensor holes in the two parts. Install shoulder screws (1-155), washers
(1-150), and nuts (1-145) (refer to Figure 7012). These screws, washers, and nuts can
be cadmium plated.

Test for the nuts - Use your hand to turn each nut as far as possible on a screw.
Discard the nut if the screw extends out of the nut.

(e) Torque each nut.

32-41-87 Page 7016

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

PISTON HOUSING
SHOULDER ASSEMBLY (1-205)
SCREW
(1-155)

NUT
(1-145)

WASHER
(1-150)
TORQUE TUBE (1-160)

Attach the Piston Housing Assembly to the Torque Tube Assembly

Figure 7012 /GRAPHIC 32-41-87-991-712-A01

Subtask 32-41-87-410-002-A01

(7) Thrust plate assembly (1-125) installation (Refer to IPL Figure 1)

(a) Put the piston housing and torque tube assembly on the work table with the piston
housing on the bottom.

(b) Slide the thrust plate assembly on the torque tube. Align the two studs with the wear
indicator pin holes in the piston housing.

32-41-87 Page 7017

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-410-003-A01

(8) Heat sink (1-105) installation (Refer to IPL Figure 1)

CAUTION: MAKE SURE THAT CARBON PARTS DO NOT HIT HARD SURFACES.
CARBON PARTS ARE EASILY DAMAGED.

(a) Slide one end plate assembly (end plate) on the torque tube (1-160) with the offset
side to point to the heat sink. Refer to Figure 7013.

NOTE: Flat or round rivet heads are permitted on all heat sink disks.

(b) Slide one rotor assembly (rotor) and one stator assembly onto the torque tube. Repeat
this until the fourth rotor assembly is installed.

Heat Sink Part Locations

Figure 7013 /GRAPHIC 32-41-87-991-713-A01

32-41-87 Page 7018

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-400-003-A01

(9) Final brake assembly (Refer to IPL Figure 1 and IPL Figure 3)

(a) Install the heat shield assembly (1-100) into the torque tube (1-160).

(b) Attach the back plate assembly (1-75) to the torque tube as follows:

CAUTION: KEEP SAE-AMS-2518 ANTI-SEIZE COMPOUND FULLY MIXED. THIS

COMPOUND THAT IS NOT MIXED CAN CAUSE INCORRECT BOLT
TENSION WHICH CAN CAUSE A BOLT TO BREAK.

1 Frequently mix SAE-AMS-2518 anti-seize compound. Fully mix the compound

in new containers that are opened.

WARNING: DO NOT GET CADMIUM IN YOUR MOUTH. CADMIUM THAT IS

SWALLOWED CAN CAUSE KIDNEY OR REPRODUCTIVE SYSTEM
DISEASE. AFTER YOU TOUCH CADMIUM PLATED PARTS, CLEAN
YOUR HANDS BEFORE YOU EAT OR SMOKE. GET SAFETY
INSTRUCTIONS FROM YOUR EMPLOYER. OBEY GOVERNMENT
AND OSHA REGULATIONS WHEN YOU DISCARD THE PARTS
THAT CONTAIN CADMIUM.

WARNING: DO NOT BREATHE CADMIUM PARTICLES, FUMES, OR DUST.

THESE PARTICLES, FUMES, OR DUST CAN CAUSE LUNG OR
KIDNEY DISEASE. IF MAINTENANCE PROCEDURES MAKE
CADMIUM PARTICLES, FUMES, OR DUST, TELL YOUR EMPLOYER
TO SUPPLY RESPIRATORS, VENTILATION, AND/OR PROCEDURES
TO PREVENT EXPOSURE TO PERSONNEL.

WARNING: THE OCCUPATIONAL, SAFETY, AND HEALTH ADMINISTRATION

(OSHA) HAS AN APPLICABLE DANGER WARNING (29 CFR
1910.1027 (M)(3)(II)) AS FOLLOWS: DANGER: CONTAINS
CADMIUM. CANCER HAZARD. AVOID CREATING DUST. CAN
CAUSE LUNG AND KIDNEY DISEASE.

CAUTION: CORRECTLY APPLY ANTI-SEIZE COMPOUND. ANTI-SEIZE

COMPOUND THAT IS NOT APPLIED CORRECTLY CAN CAUSE
INCORRECT BOLT TENSION WHICH CAN CAUSE A BOLT TO
BREAK.

CAUTION: APPLY ONLY A SPECIFIED ANTI-SEIZE COMPOUND. A

2 Apply a layer of specified anti-seize compound to the threads and under the
head of each bolt (1-70) (refer to Figure 7014).

32-41-87 Page 7019

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

APPLY ANTI-SEIZE COMPOUND

TO THESE SURFACES

Application of Anti-seize Compound

Figure 7014 /GRAPHIC 32-41-87-991-714-A01

3 Attach the back plate assembly to the torque tube with the bolts (1-70). Torque
the bolts in the sequences that are shown in Figure 7015.

251,99 (9.921)
1 251,99 (9.921) 1 DIA. (REF.)
7 10
DIA. (REF.)
5 2
3 9

10 9 8 3

4 4
6 7

2 8 6 5

PRELIMINARY TORQUE SEQUENCE FINAL TORQUE SEQUENCE

(CRISSCROSS) (CLOCKWISE OR COUNTERCLOCKWISE)

Bolt Torque Sequence for the Installation of the Backplate Assembly

Figure 7015 /GRAPHIC 32-41-87-991-715-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

CAUTION: INSTALL LOCKWIRE TO MAKE THE PIGTAIL POINT TO THE OUTER

DIAMETER OF THE BRAKE ASSEMBLY. THE INCORRECT
LOCATION OF A PIGTAIL CAN CAUSE DAMAGE TO THE WHEEL
ASSEMBLY.

4 Lockwire the bolts (1-70) together in pairs as shown in Figure 7016.

Lockwire Pattern of Bolts (1-70) and Screw (1-60)

Figure 7016 /GRAPHIC 32-41-87-991-716-A01

(c) Temperature sensor (1-65) installation

CAUTION: MAKE SURE THAT THE CORRECT TEMPERATURE SENSOR (1-65)

IS INSTALLED. DO NOT INSTALL SIMILAR SENSORS FROM OTHER
BRAKE ASSEMBLIES FOR AIRPLANE MODELS A330, A340, A321,
AND A320. INCORRECT TEMPERATURE SENSORS GIVE
INCORRECT TEMPERATURE INDICATIONS IN THE COCKPIT.

1 Put the brake assembly on the work table with the back plate assembly (1-75)
on the bottom.

2 Put the temperature sensor in the hole in the torque tube (1-160).

3 Apply a specified anti-seize compound to the threads of the cap screw (1-60).
The cap screw can be cadmium plated.

4 Install the cap screw.

5 Torque the cap screw.

6 Lockwire the cap screw as shown in Figure 7016.

32-41-87 Page 7021

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

(d) Bleeder valve (1-175) installation

1 Install one bleeder valve and O-ring (1-185) in each of the two bleeder ports of
the piston housing assembly (1-205).

2 Torque each bleeder valve.

3 Lockwire each bleeder valve to the piston housing assembly.

4 Install one valve cap (1-180) on each bleeder valve.

5 Torque each valve cap.

(e) Hydraulic fitting (1-190) assembly

1 If a hydraulic fitting is disassembled, apply hydraulic fluid to new O-rings (3-15,

3-30) and install the O-rings. Refer to IPL Figure 3.

2 Torque the nipple (3-10) in the nipple end (3-35).

(f) Hydraulic fitting (1-190) installation

1 Install one hydraulic fitting and O-ring (1-195) in each of the two inlet ports of
the piston housing assembly (1-205).

2 Torque each hydraulic fitting.

3 Lockwire each hydraulic fitting to the piston housing assembly.

4 Install one protective cap (3-5) on each hydraulic fitting.

(g) Wear indicator pins (1-115) installation

1 Slide the flange end of each wear indicator pin (1-115) through an
adapter (1-120).

2 Insert each wear indicator pin and adapter assembly through the piston
housing assembly (1-205). Put each adapter on a stud on the thrust plate
assembly (1-125).

3 Install a cotter pin (1-110) through each adapter and stud. Bend the ends of
each cotter pin around the adapter. The cotter pins can be cadmium plated.

Subtask 32-41-87-700-004-A01

(10) Test of the brake

(a) Do a test of the brake (refer to the TESTING AND FAULT ISOLATION section)
(Ref.: TASK 32-41-87-700-801-A01).

32-41-87 Page 7022

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

FITS AND CLEARANCES

TASK 32-41-87-820-801-A01
1. Fits and Clearances

A. Procedure to use the Fits and Clearances Table (Refer to IPL Figure 1 and IPL Figure 2)

Subtask 32-41-87-820-001-A01

(1) Refer to Figure 8001 to see the location of the parts in the table.

NOTE: When parts with satisfactory dimensions are assembled, the mating parts have the
correct fits and clearances. You cannot measure these fits and clearances on an
assembled brake assembly.

LIMITS ON NEW PARTS LIMITS ON USED PARTS

PART
NAME MEASURED DIMENSIONS ASSEMBLY DIMENSIONS MM ASSEMBLY
AND IPL LOCATION MM (INCHES) CLEARANCE (INCHES) CLEARANCE
ITEM NO. (REFER TO (REFER TO
MIN. MAX. THE NOTE) MIN. MAX. THE NOTE)

33,96) 34,06 33,96 34,09

SMALL I.D. --- ---
SLEEVE (1.337) (1.341) (1.337) (1.342)
(2-50) 40,44 40,49 40,44 40,54
LARGE I.D. --- ---
(1.592) (1.594) (1.592) (1.596)

33,20 33,30 33,15 33,30

SMALL O.D. --- ---
PISTON (1.307) (1.311) (1.305) (1.311)
(2-115) 40,36 40,39 40,26 40,39
LARGE O.D. --- ---
(1.588) (1.590) (1.585) (1.590)

6,312 6,439 6,312 6,439

I.D. --- ---
BUSHING (0.2485) (0.2535) (0.2485) (0.2535)
(2-95) 12,29 12,45 12,29 12,45
O.D. --- ---
(0.484) (0.490) (0.484) (0.490)

TORQUE
LUGS ON
19,81 19,99 19,68 19,99
TORQUE WIDTH --- ---
(0.780) (0.787) (0.775) (0.787)
TUBE
(1-160)
PISTON
CAVITIES
OF
I.D. OF SEAL 50,80 50,85 50,80 50,88
PISTON --- ---
SURFACE (2.000) (2.002) (2.000) (2.003)
HOUSING
ASSEM.
(1-205)

32-41-87 Page 8001

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

1,14 (0.045) MIN.

21,08 (0.830) MAX.

Measurement Locations on Parts

Figure 8001 /GRAPHIC 32-41-87-991-801-A01

32-41-87
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Page 8002
Dec 20/04
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Subtask 32-41-87-820-002-A01

(2) Torques (Refer to IPL Figure 1, IPL Figure 2, and IPL Figure 3)

IPL ITEM NO. NOMENCLATURE SPECIFIED

AND ITEM NO. (PART NAME) TORQUE VALUE COMPOUND

SAE-AMS-2518
6,8 Nm (60 pound-inches) or
1-25 Nut Fel-Pro C5A

5,8 Nm (51 pound-inches) MIL-PRF-83483

SAE-AMS-2518
47 Nm (35 pound-feet) or
1-40 Nut Fel-Pro C5A

39 Nm (29 pound-feet) MIL-PRF-83483

SAE-AMS-2518
2,6 Nm (23 pound-inches) or
1-60 Cap Screw Fel-Pro C5A

2,1 Nm (1 9 pound-inches) MIL-PRF-83483

40,7 Nm (30 pound-feet)

(Preliminary) SAE-AMS-2518
or
81 Nm (60 pound-feet) Fel-Pro C5A
(Final)
1-70 Bolt
34 Nm (25 pound-feet)
(Preliminary)
MIL-PRF-83483
67,8 Nm (50 pound-feet)
(Final)

6,8 Nm (60 pound-inches) SAE-AMS-2518

1-145 Nut or
5,8 Nm (51 pound-inches) Fel-Pro C5A

1-170 Adjuster Assembly 57 Nm (42 pound-feet) None

1-175 Bleeder Valve 14 Nm (125 pound -inches) None

--- Bleeder Valve Stem 7,0 Nm (62 pound-inch) None

1-180 Valve Cap 1,0 Nm (8,5 pound-inches) None

1-190 Hydraulic Fitting 18,1 Nm (160 pound-inches) None

2-25 Self-Locking Nut 7,9 Nm (70 pound-inches) None

3-10 Nipple 18,1 Nm (160 pound-inches) None

32-41-87 Page 8003

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INTENTIONALLY BLANK
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
Part Number 2-1684

TEMPORARY REVISION NO. 32-3

Page Affected: 9001

Changes: Revise the Special Tools, Fixtures, and Equipment Table as follows:

TASK 32-41-87-940-801-A01

1. Special Tools, Fixtures and Equipment

A. General

(1) Common tools and equipment are not shown below. The special tools, fixtures,
and equipment shown below are not available from Goodrich Corporation.

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

(2) Locally make the special tools, fixtures, and equipment (refer to the drawings in
this section).

(3) Hammer stamp the tool part number on each tool to help the maintenance
personnel find the correct tool.

FIGURE TOOL PART (1) Optional

TOOL DESCRIPTION
NUMBER NUMBER (2) Necessary
9001 114-291 Adjuster assembly / disassembly tool (2)
9002 114-293 Backup ring installation tool (2)
9003 114-1159 Backup ring sizing tool (1)
9004 114-325 Piston installation support tool (2)
9005 114-326 Piston installation bullet tool (2)
9006 114-327 Piston installation guide tool (2)
9007 114-245 Adjuster pin installation tool (2)
Radial riveting peen that attaches the
9008 114-239 (2)
back plate pads to the backplate
Radial riveting anvil that attaches the
9009 114-241 (2)
back plate pads to the back plate
9010 114-330 High-pressure leak test shims (2)
Quick-connect hydraulic fitting (refer
9011 HTE711-59U to page 10004 for the address of (2)
Eaton Aerospace LTD)

UTC AEROSPACE SYSTEMS PROPRIETARY

32-41-87 Page 2 of 4
Oct 28/20
U.S. Export Classification: EAR 9E991
**Printed copies are considered UNCONTROLLED – Verify current issue before use**
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

SPECIAL TOOLS, FIXTURES, EQUIPMENT AND CONSUMABLES

TASK 32-41-87-940-801-A01
1. Special Tools, Fixtures and Equipment

A. General

(1) Common tools and equipment are not shown below. The special tools, fixtures, and
equipment shown below are not available from Goodrich Corporation.

NOTE: Equivalent alternatives are permitted for the items in the list that follows:

(2) Locally make the special tools, fixtures, and equipment (refer to the drawings in this section).

(3) Hammer stamp the tool part number on each tool to help the maintenance personnel find the
correct tool.

FIGURE TOOL PART (1) Optional

TOOL DESCRIPTION
NUMBER NUMBER (2) Necessary

9001 114-291 Adjuster assembly / disassembly tool (2)

9002 114-293 Backup ring installation tool (2)

9003 114-1159 Backup ring sizing tool (1)

9004 114-325 Retaining ring pliers (2)

9005 114-326 Piston installation bullet tool (2)

9006 114-327 Piston installation guide tool (2)

9007 114-245 Adjuster pin installation tool (2)

Radial riveting peen that attaches the

9008 114-239 (2)
back plate pads to the backplate

Radial riveting anvil that attaches the

9009 114-241 (2)
back plate pads to the back plate

9010 114-330 High-pressure leak test shims (2)

Quick-connect hydraulic fitting (refer to

9011 HTE711-59U page 10004 for the address of (2)
Eaton Aerospace LTD)

32-41-87 Page 9001

Dec 20/04
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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TOOL P/N: 114-921

MATERIAL: STEEL
18,3 - 19,8
(0.72 - 0.78)
REFER NOTE 1 TYP.

18,3 - 19,8
11,94 - 12,19 (0.72 - 0.78) 15,8 - 17,3
(0.470 - 0.480) (0.62 - 0.68)
DIA. TYP. DIA. TYP.

NOTES:
1. Length and diameter to fit the arbor press or drill press
2. Break all sharp edges

Adjuster Assembly / Disassembly Tool

Figure 9001 /GRAPHIC 32-41-87-991-901-A01

32-41-87
This document is subject to the controls and restrictions on the first page.
Page 9002
Dec 20/04
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
Part Number 2-1684

TEMPORARY REVISION NO. 32-3

Page Affected: 9002

Changes: Revise Figure 9001 as follows:

TOOL P/N: 114-291

MATERIAL: STEEL
18,3 - 19,8
(0.72 - 0.78)
REFER NOTE 1 TYP.

11,94 - 12,19 18,3 - 19,8 15,8 - 17,3

(0.470 - 0.480) (0.72 - 0.78) (0.62 - 0.68)
DIA. TYP. TYP. DIA. TYP.

NOTES:
1. LENGTH AND DIAMETER TO FIT THE ARBOR PRESS OR DRILL PRESS.
2. BREAK ALL SHARP EDGES.
3. DIMENSIONS SHOWN ARE IN MM (INCHES).

Adjuster Assembly / Disassembly Tool

Figure 9001 /GRAPHIC 32-41-87-991-901-A01

UTC AEROSPACE SYSTEMS PROPRIETARY

32-41-87 Page 3 of 4
Oct 28/20
U.S. Export Classification: EAR 9E991
**Printed copies are considered UNCONTROLLED – Verify current issue before use**
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

DIA.

R. DIA.

DIA.
DIA.

DIA.

VIEW 'A-A'

Backup Ring Installation Tool

Figure 9002 /GRAPHIC 32-41-87-991-902-A01

32-41-87 Page 9003

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Backup Ring Sizing Tool

Figure 9003 /GRAPHIC 32-41-87-991-903-A01

32-41-87
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Page 9004
Dec 20/04
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TOOL P/N: 114-325 15,62 - 16,13

(0.615 - 0.635)
MATERIAL: ALUMINUM or DELRIN DIA.

151,6 - 153,2
31,75 - 32,26
(5.97 - 6.03)
(1.250 - 1.270)
DIA.
DIA.

NOTE: Break all sharp edges

Piston Installation "Support" Tool

Figure 9004 /GRAPHIC 32-41-87-991-904-A01

TOOL P/N: 114-326

MATERIAL: ALUMINUM or DELRIN

R. 0,8 - 2,3 (0.03 - 0.09)

33,27 - 33,32 28,42 - 28,47

(1.310 - 1.312) (1.119 - 1.121)
DIA. DIA.

DIA.
R.

NOTE: Break all sharp edges

Piston Installation "Bullet" Tool

Figure 9005 /GRAPHIC 32-41-87-991-905-A01

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

DIA.
4 LOCATIONS
DIA.

DIA. DIA.

REF.

4 LOCATIONS

Piston Installation "Guide" Tool

Figure 9006 /GRAPHIC 32-41-87-991-906-A01

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
Part Number 2-1684

TEMPORARY REVISION NO. 32-3

Page Affected: 9007
Changes: Revise Figure 9007 as follows:

TOOL P/N: 114-245

MATERIAL: ALUMINUM OR DELRIN
6,312 - 6,337 (0.2485 - 0.2495) DIA FOR 1 LENGTH
1,8 - 3,3 6,27 - 6,32 (0.247 - 0.249) FOR THE REMAINDER
(0.07 - 0.13) 4,80 - 4,85
SPHERICAL 4,67 - 5,49 (0.189 - 0.191)
DIAMETER 1 DIA.
(0.184 - 0.216)

BLEND AND POLISH 12,29 - 13,11

(0.484 - 0.516)
22,45 - 23,27
(0.884 - 0.916)
31,34 - 32,16
NOTES: (1.234 - 1.266)
1. BREAK ALL SHARP EDGES.
2. DIMENSIONS SHOWN ARE IN MM (INCHES).
Adjuster Pin Installation Tool
Figure 9007 /GRAPHIC 32-41-87-991-907-A01

TOOL P/N: 114-239

MATERIAL: W1 OR W2 TOOL STEEL
HARDEN TO Rc 50-55
ANGLE EQUAL TO THE “WOBBLE ANGLE”
OF THE RIVET MACHINE

LENGTH AND DIAMETER

TO FIT THE
RIVET MACHINE

5,84 - 6,35
(0.230 - 0.250) 11,81 - 12,32
DIA. (0.465 - 0.485)
NOTES:
1. BREAK ALL SHARP EDGES.
2. DIMENSIONS SHOWN ARE IN MM (INCHES).
Radial Riveting Peen
Figure 9008 /GRAPHIC 32-41-87-991-908-A01

UTC AEROSPACE SYSTEMS PROPRIETARY

32-41-87 Page 4 of 4
Oct 28/20
U.S. Export Classification: EAR 9E991
**Printed copies are considered UNCONTROLLED – Verify current issue before use**
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TOOL P/N: 114-325

MATERIAL: ALUMINUM or DELRIN

NOTE: Break all sharp edges

Adjuster Pin Installation Tool

Figure 9007 /GRAPHIC 32-41-87-991-907-A01

DIA.

Radial Riveting Peen

Figure 9008 /GRAPHIC 32-41-87-991-908-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

DIA.

Radial Riveting Anvil

Figure 9009 /GRAPHIC 32-41-87-991-909-A01

TOOL P/N: 114-330

MATERIAL: ALUMINUM

280,4 - 281,9 418,1 - 419,6

(11.04 - 11.10) (16.46 - 16.52)
DIA. DIA.

0,76 - 2,29 1,27 - 1,78

(0.030 - 0.090) (0.050 - 0.070)

NOTE: Break all sharp edges

High-Pressue Leak Test Shims

Figure 9010 /GRAPHIC 32-41-87-991-910-A01

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TASK 32-41-87-940-802-A01
2. Aqueous Cleaner Consumables (Refer to paragraph 3. "Other Consumables")

NOTE: Equivalent replacements are permitted for the items in the list that follows:

RECOMMENDED
CLEANING PRODUCT
CONCENTRATION & VENDOR
NAME
TEMPERATURE

Applied 4-204 Cleaner 30y at 49 LC (120 LF) Applied Chemical Technologies, Inc.
1045 Georgetown Road
Bldg. C-4
Lexington, Kentucky 40511
U.S.A.

Aquaspray 102 5y at 54 LC (130 LF) Hubbard-Hall Inc.

1101 Compton Bridge Road
Inman, South Carolina 29349
U.S.A.

Ardrox 6333 20y at 66 LC (150 LF) Chemetall Oakite Inc.

50 Valley Road
Berkeley Heights, New Jersey 07922
U.S.A.

Armakleen M-HP2 3y at 54 LC (130 LF) Church & Dwight Co. Inc.

or 10y at 71 LC 469 North Harrison Street
(160 LF) Princeton, New Jersey 08543
U.S.A.

Big Blue 2 oz. / gal. at B & B Tritech, Inc.

66 LC (150 LF) 875 West 20th Street
Hialeah, Florida 33010
U.S.A.

Brulin 1990 GD 3y at 54 LC (130 LF) Brulin & Co., Inc.

or 10y at 66 LC P.O. Box 270
(150 LF) Indianapolis, Indiana 46206
U.S.A.
Brulin 815 GD 5y at 54 LC (130 LF)
or 10y at 71 LC
(160 LF) or 20y at
82 LC (180 LF)

Cal Clean 657-LF 1y at 49 LC (120 °F) Calvary Industries

9233 Seward Road
Fairfield, Ohio 45014
U.S.A.

Calgon 6215 3y at 54 LC (130 LF) Calgon Corporation

& at 71 LC (160 LF) P.O. Box 1346
Pittsburgh, Pennsylvania 15024
U.S.A.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

RECOMMENDED
CLEANING PRODUCT
CONCENTRATION & VENDOR
NAME
TEMPERATURE

Cee-Bee A7X7 10y at 54 LC McGean-Rohco Inc.

(130 LF) The Republic Bldg, Suite 1100
25 West Prospect Avenue
Cee-Bee 280 10y at 54 LC Cleveland, Ohio 44115-1000
(130 LF) U.S.A.
Cee-Bee 300LF 10y at 60 LC
(140 LF)

Dubois Multi-Terj 1012 1y at 43 LC (110 LF) Dubois Chemicals

3630 East Kemper Road
Cincinnati, Ohio 45241
U.S.A.

Eldorado ED-306LF 3y at 54 LC (130 LF) Eldorado Chemical Company

& at 82 LC (180 LF) P.O. Box 34837
San Antonio, Texas 78265
U.S.A.

Magnus HDL-330 10y at 66 LC Mag-Chem Inc.

(150 LF) 190 Boul. Industries
Boucherville, Quebec
Magnus Soluwax 10y at 54 LC Canada J4B 2X3
(130 LF)

Magnus Aerodet 10y at 54 LC

(130 LF)

Mirachem 500 15y at 43 LC Mirachem Corporation

(110 LF) 1045 S. Edward Road
Tempe, Arizona 85281
Mirachem 750LF 25y at 63 LC U.S.A.
(145 LF)

Rainbow Jet 5y and 9y at 60°C ADN Chemicals

(140 LF) 2720 Reynolds Road
Winston Salem, North Carolina 27106
U.S.A.

Ram Wash H.D. 17y at 71 LC Ram Environmental Technologies, Inc.

(160 LF) 5200 Cahaba River Road
Birmingham, Alabama 35243
U.S.A.

SAG 710 (anti-foam) 0.8 oz./gal at 60 LC Witco Corporation

(140 LF) One American Lane
Greenwich, Connecticut 06831
U.S.A.

Superclean RP 98 A 12 oz./gal. at Lubrichem Environmental

21 - 27 °C (71 - 82 °F) 2108 Plantside Drive
Louisville, Kentucky 40299
U.S.A.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

RECOMMENDED
CLEANING PRODUCT
CONCENTRATION & VENDOR
NAME
TEMPERATURE

Turco 3878 LF-NC 20y at 60 LC LA CIE Deane & Co.

(140 LF) 190 Oneida Drive
Pointe-Claire, Quebec
Turco 6751-L 2y at 60 LC (140 LF) Canada H9R 1AB
Turco 6849 4y at 63 LC (145 LF)
or 20y at 60 L - 71 LC
(140 L - 160 LF)

Turco Aviation 2 oz. /gal. at 66 LC

(150 LF)

Turco Sprayeze NPLT 3y at 54 LC (130 LF)

or 10y at 71 LC
(160 LF)

ZOK27 20y at 71 LC Zokman Products

(160 LF) 1220 East Gump Road
Fort Wayne, Indiana 46845
U.S.A.
Tel: 800-727-6027
Fax: 800-844-3227

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

TASK 32-41-87-940-803-A01
3. Other Consumables (refer to paragraph 2. "Aqueous Cleaner Consumables")

NOTE: You can replace some of the materials shown below with equivalent materials that are permitted
by the specification. Equivalent materials are not permitted for hydraulic fluid and anti-seize
compound. If you cannot locally purchase materials, purchase the materials from the vendors
shown below.

VENDOR'S NAME AND

TYPE OF CONSUMABLE MATERIAL NAME
ADDRESS

Degreasing Solvent
Approved Vendor
MIL-PRF-680 Type II or III
Cleaner
Butyl Alcohol
(Solvent Based)
Naphtha CommerciallyAvailable
TT-N-95 OR TT-N-97

Plastic Media
MIL-P-85891 Type II (maximum Approved Vendor
Paint Removal Abrasive media hardness of 3.5 MOH)

Walnut Hulls A-A-1722

Type II or lll, Grade 20/30

Sodium Bicarbonate

Paint Remover SAE-AMS-1375

Commercially Available
Corrosion-Removal SAE-AMS-1640
Product

ASTM E1417 Type I, Method A,

Penetrant Fluid
Level 2

Conversion Coat MIL-C-5541 Class 1A Approved Vendor

TT-P-1757B Commercially Available

Alkyd Primer
Type I, Class C or N

Approved Vendor or Hentzen

Coatings, Inc.
MIL-PRF-23377 Type I, Class C1, 6937 West Mill Road
Thinner-reducible
C2, or N Milwaukee, Wisconsin 53218
Epoxy Polyamide Primer
(Class N is non-chromate) U.S.A.
Tel: 414-353-4200
www.hentzen.com

MIL-PRF-85582 Type I, Class C1, Deft, Inc.

C2, or N 17451 Von Karman Avenue
Water-reducible Epoxy (Class N is non-chromate) Irvine, California 92614
Polyamide Primer Product No. 44-GN-007 (Class C1) U.S.A.
Product No. 44-GN-098 (Class N) Tel: 800-544-3338
www.deftfinishes.com

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

VENDOR'S NAME AND

TYPE OF CONSUMABLE MATERIAL NAME
ADDRESS

TAT Lubricants, Inc.

22 Parkway Circle
Unit 12
Lubricant UniFlor®, P/N NYE8512S New Castle, Delaware 19720
U.S.A.
Tel: 302-326-0200
Fax: 302-326-0400

MIL-PRF-85285 Approved Vendor

White
Urethane Paint (FED-STD-595 color No. 17925)

Light Gray
(FED-STD-595 color no. 16515)

Ashland Specialty Chemical

Company
Division of Ashland Inc.
P.O. Box 2219
Thinner MIL-T-81772 Types II & III
Columbus, Ohio 43216
U.S.A.
Tel: 800-228-0965
www.ashland.com

“VHT” Paint SP-117 Advance Packaging and

Products Co.
Paint Product 16131 South Maple Avenue
Gardena, California 90248
U.S.A.

Base 683-3-2 TC Specialties

Catalyst X-310-A 3911-C East LaPalma
Sealant
Anaheim, California 92807
U.S.A.

Anti-seize Compound Armite Laboratories 1560-T

SAE-AMS-2518 Superior Avenue A-4
Costa Mesa, California 92627
U.S.A.
Assembly Products Tel: 949-646-9035
Fax: 949-646-8319

Anti-seize Compound
MIL-PRF-83483
Commercially Available
Anti-seize Compound
Fel-Pro C5A

Phosphate Ester
Hydraulic Fluid Commercially Available
Product No. NSA 307-110

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

STORAGE (INCLUDING TRANSPORTATION)

TASK 32-41-87-550-801-A01
1. Storage

A. Reason for the Job

Self-explanatory

B. Job Set-up Information

(1) Tools, fixtures, and equipment

Not applicable

(2) Consumables

Not applicable

(3) Referenced information

REFERENCE DESCRIPTION

SAE-ARP-5316 Shelf-life limits and storage

recommendations for elastomeric
seals and seal assemblies

C. Job Set-up

Not applicable

D. Storage Procedures (Refer to IPL Figure 1, IPL Figure 2, and IPL Figure 3)

(1) Install a protective cap (2-25) on the temperature sensor (1-65) and a protector cap (3-5) on
each hydraulic fitting (1-190).

(2) There are no environmental restrictions different from those that are applicable for other
aircraft brake assemblies. Do not let contamination collect on the carbon parts (refer to the
CLEANING section for the removal of contamination).

(3) Keep the parts away from: flow of air, radiation, ozone (made by electric arcs, fluorescent
lamps, and other electrical equipment), and other contamination.

(4) Keep rubber parts in a dark and dry area that is not more than 38 °C (100 °F).

NOTE: Refer to Goodrich Service Letter No. 1854 for the limit on storage life of
O-rings (1-165, 1-185, 1-195, 2-60, 2-65, 2-85, 3-15, 3-30) that are not installed
(reference: SAE-ARP5316).

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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

ILLUSTRATED PARTS LIST

TASK 32-41-87-871-801-A01
1. Introduction

CAUTION: GOODRICH ASSUMES NO LIABILITY WHATSOEVER, WHETHER CONTRACTUAL,

WARRANTY, TORT OR OTHERWISE, FOR ANY FEDERAL AVIATION ADMINISTRATION
SANCTIONS, PRODUCT MALFUNCTIONS, PROPERTY DAMAGE, PERSONAL
INJURIES, OR SIMILAR INCIDENTS THAT OCCUR AFTER SUBSTITUTION OF PARTS
THAT ARE NOT APPROVED BY GOODRICH, OR SUBSTITUTION OF PARTS WITH
ALTERATIONS THAT ARE NOT APPROVED BY GOODRICH MANUALS OR OTHER
WRITTEN PROCEDURES THAT ARE ISSUED BY GOODRICH.

CAUTION: THE USE OF REPLACEMENT PARTS THAT ARE NOT APPROVED BY GOODRICH FOR
INSTALLATION IN A SPECIFIED ASSEMBLY WILL AUTOMATICALLY VOID ALL
WARRANTIES EXTENDED BY GOODRICH.

A. Purpose

This section identifies the parts of the assemblies that you can disassemble, repair or
replace, and assemble.

B. Description of Data

(1) Item Numbers

An item number identifies a part in all sections of the manual. The item number for a part
usually does not change, but you can add alpha variants of the item number. Refer to
paragraph 2.B.

A figure number is shown before the item number when there is more than one
figure supplied in the illustrated parts list.

(2) Alpha Variant Item Numbers

An "Alpha Variant" is an alphabetic letter which follows the item number. This letter "varies"
(changes) when that item number is shown again. This letter is shown in a figure to identify a
part that has a different shape or location than the initial part.

The letters "B" through "Z", but not I and O, follow repeated item numbers when
the parts list must show:

(a) Added items

(b) Items that a Service Bulletin modifies

(c) Different configurations

(d) Alternate or Optional parts

(e) Improved parts that a Service Bulletin does not introduce

(3) Parts that are not shown in an exploded view have a dash (-) before the item number.

(4) Indenture System to Show The Parts in an Assembly or Subassembly

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

The parts list shows how parts are related to other parts in each assembly or subassembly.
The periods before the part name show the number of spaces that the part name is indented
in the NOMENCLATURE column. Each part or subassembly is related to the next higher
subassembly or assembly as follows:

1 2 3 4 5 6 7 (Spaces that the part name is indented)

Assembly (End item)
. Detail parts of the assembly
. Subassembly
. Parts that attach the subassembly
. . Detail parts for the subassembly
. . . Detail installation parts for the subassembly (included when installation
parts are returned to the maintenance area as part of the assembly.)

(5) Parts Replacement Data:

You can interchange parts when you obey the terms that follow. These terms are shown in
the NOMENCLATURE (part name) column of the parts list.

TERM ABBREVIATION DEFINITION

Alternate ALT This part can replace the specified part, but has a
different dimension, is installed differently, or you
must add or remove other parts.

Optional OPT This part is optional and interchangeable

with the specified part.

Superseded by SUPSD BY A different part replaces this part and the parts are
not interchangeable.

Supersedes SUPSDS This different part replaces a part and the parts are
not interchangeable.

Replaced by REPLD BY A different part replaces this part and the

parts are interchangeable.

Replaces REPLS This different part replaces a part and the parts are
interchangeable.

Vendor V Commercial and Government Entity (CAGE)

number for the manufacturer of the part.

Non-Procurable NON-PROC The part cannot be purchased - purchase the

subsequent higher assembly.

(6) Service Bulletins that are Included

(a) A Service Bulletin can add, remove, change, or replace assemblies, subassemblies,
and detail parts. The NOMENCLATURE (part name) column shows "PRE SB XXX"
(pre-Service Bulletin) when identification of the initial configuration is necessary.
"POST-SB XXX" (post-Service Bulletin) is shown to identify affected assemblies,
subassemblies, or detail parts.

(b) PRE SB XXX or POST SB XXX are not shown for the conditions that follow:

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

1 The "EFF. CODE" column clearly shows the pre- or post-Service Bulletin
condition of the assemblies, subassemblies, or detail parts.

2 The Service Bulletin changes the end-item assembly and no change is

necessary to its part number. There is no factory-manufactured equivalent of
the changed assembly.

(c) "PRE SB XXX" is not shown, and "POST SB XXX" is shown, when a Service Bulletin
changes a subassembly or detail part with no change to its part number. An alpha
variant letter is also added to the item number.

(7) Effectivity Code

When there is more than one end-item assembly shown in the parts list, a reference letter
(A,B,C, etc.) is shown in the EFF. CODE column for each end-item assembly. This same
reference letter is shown in the EFF. CODE column for each detail part or subassembly that
you can install in the end-item assembly with the same reference letter. You can install detail
parts and subassemblies in all end-item assemblies if no reference letter is shown.

(8) Quantity For Each Assembly

The UNITS FOR EACH ASSY column usually shows the full number of parts that are
necessary for each assembly or subassembly.

The letters "AR" identify the parts that are installed "as required" (for example: lock wire).

The letters "RF" identify the parts that are given only for reference.

C. Vendors

If a part has a vendor code number (V92555, for example) in the “NOMENCLATURE” column of the
ILLUSTRATED PARTS LIST, that part is FAA approved as part of the Goodrich Quality Assurance
System. Sources of these parts, other than Goodrich, must have alternate FAA approval [refer to
Federal Aviation Regulations (14 CFR Part 21)].

VENDOR INTERNET
CAGE CODE NO. VENDOR NAME AND ADDRESS
ADDRESS

27783 Schrader-Bridgeport International, Inc.

1609 Airport Road
P.O. Box 5036 ----
Monroe, North Carolina 28110
U.S.A.

92555 The Lee Company

2 Pettipaug Road
www.theleeco.com
Westbrook, Connecticut 06498-1591
U.S.A.

HTE P/N Eaton Aerospace LTD.

(Refer to IPL Figure 3) Abbey Park Southampton Rd
www.eaton.com
Titchfield Fareham PO14 4QA
United Kingdom

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

D. “True” (Full) Part Numbers

True part numbers for some assemblies contain an option number (OPT1, OPT2, etc.)
that is not shown in the PART NUMBER column. Use the true part number as shown in the
NOMENCLATURE column in orders for assemblies with these option numbers.

EXAMPLE: Item 205A, shown as “266-236” in the PART NUMBER column has a full
part number shown as “True P/N is 266-236OPT1” in the NOMENCLATURE column of IPL Figure
1.

True part numbers that contain a dash (-) between a letter and number are not permitted by ATA.
Use the true part number as shown in the NOMENCLATURE column to order part with a dash (-) in
this location.

EXAMPLE: Item 135A, shown as “WS175PAS17” in the PART NUMBER column has a between a
letter and a number. “True P/N is WS-175-PA-S17” in the NOMENCLATURE column of IPL
Figure 1 shows the full part number.

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Part Number Airline Stock Fig Item Total Required

No.

AN960C10L 1 85A 12
AN960XC10L 1 85B 12
FN12M02 2 25A 1
HTE1001V7 3 20A 1
HTE711-59V 1 190A 2
HTE711-59V 3 1A RF
HTE717V 3 5A 1
HTE7300E3-012 3 30A 1
HTE7300E3-015 3 15A 1
HTE7300E8-012 3 30B 1
HTE7300E8-015 3 15B 1
HTE760-1V3 3 10A 1
HTE761V8 3 25A 1
HTE762-52V8 3 35A 1
MS16625-3100 2 75B 1
MS16625-4112 2 100A 1
MS20002-10 1 10A 3
MS20427M6-18 1 80A 12
MS20995C32 1 55A AR
MS21043-4 1 25A 6
MS21043-4 1 145A 3
MS24665-134 1 110A 2
NAS1102E4-16 1 35A 6
NAS1149C0432R 1 30A 6
NAS1149C0432R 1 150B 3
NAS1351C4H8S 1 60A 1
NAS1602-906 1 195B 2
NAS1611-015 1 185B 1
NAS1612-6 1 185C 1
NAS1612-6 1 195A 2
NAS1805-6P 1 40A 9
N5000-100 2 75A 1
PLGA2180010 1 215A 16
PLGA2280010 1 215B AR
PLGM0600010A 1 215C AR
RS175SCP 1 135B 14
S33865-14W10 2 55A 1
WS175PAS17 1 135A 14
107-487 1 170A 14
107-487 2 1A RF
113-336 2 105A 1
115-423 1 130A 14
130-17 2 30A 1
2-1684 1 1A RF
20-520 1 115A 2
20-739 2 40A 1
245-238 2 10A 1
26-395 2 95A 1
260-843-1 1 220A 1
266-236 1 205A 1
NUMERICAL INDEX
Page 10005
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GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

Part Number Airline Stock Fig Item Total Required

No.

294-12 1 75B 1
294-58 1 75A 1
294-6 1 140A 1
294-9-1 1 125A 1
319-40 1 160B 1
319-41 1 160A 1
378-55 1 100A 1
40-676 2 110A 1
43-1345 1 155A 3
43-1348 1 20A 3
43-1349 1 70A 10
45-295 2 35A 1
466-19 1 65B 1
466-19-1 1 65A 1
50-577 1 210A 1
50-615 2 20A 1
50-830 1 200A 1
521-11 1 50A 9
537-67 1 105B 1
537-68 1 105A 1
54-620 2 50A 1
549-18 2 90A 2
549-61 2 70A 1
549-69 2 5A 1
55-140 2 15A 1
551-1 1 90A 12
56-842 2 80A 1
56-881 1 15A 3
56-971 2 45B 1
56-973 2 45A 1
63-523 1 5A 3
68-1449 2 60A 1
68-1519 2 85A 1
68-1580 2 85B 1
68-1581 1 165A 14
68-1582 2 65A 1
74-970 2 115A 1
7612 1 180A 1
798A 1 175A 2
798A-15 1 185A 1
80-741 1 30B 6
80-741 1 150A 3
80-742 1 45A 9
93-1037 1 95A 1
93-952 1 95B 1
95-569 1 120A 2

NUMERICAL INDEX
Page 10006
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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

this is a title

40 30
45 15 145
180 150
50
25 175 190
195
20 185

10 210
35 5
200
170
165

215

205, 220
100

155 160

70
75, 95

55
60 65 105

115 110

120
85

90
80

130
135
125, 140

2-1684 Brake Assembly

Figure 1/GRAPHIC 32-41-87-991-1001-A01

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COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

AIRLINE USAGE UNITS

FIG.-ITEM PART NUMBER PART NOMENCLATURE FROM PER
NUMBER 1234567 TO ASSY

1 -1A 2-1684 MLG Brake Assembly RF

5A 63-523 .Nut, Self-Locking 3

(Part can be cadmium plated)

10A MS20002-10 .Washer, Flat 3

(Part can be cadmium plated)

15A 56-881 .Retainer, Bolt 3

20A 43-1348 .Bolt 3

(Part can be cadmium plated)

25A MS21043-4 .Nut, Self-Locking 6

(Part can be cadmium plated)

30A NAS1149C0432R .Washer, Flat 6

-30B 80-741 .Washer, Flat 6

(OPT to Item 30A)

35A NAS1102E4-16 .Screw 6

(Part can be cadmium plated)

40A NAS1805-6P .Nut, Self-Locking 9

45A 80-742 .Washer, Flat 9

50A 521-11 .Stud 9

55A MS20995C32 .Lockwire AR

60A NAS1351C4H8S .Screw, Cap 1

(Part can be cadmium plated)

65A 466-19-1 .Sensor, Temperature 1

-65B 466-19 .Sensor, Temperature 1

(OPT to Item 65A)

70A 43-1349 .Bolt 10

75A 294-58 .Plate Assembly, Back 1

-75B 294-12 .Plate Assembly, Back 1

(ALT to Item 75A)

80A MS20427M6-18 ..Rivet 12

85A AN960C10L ..Washer, Flat 12

- ITEM NOT ILLUSTRATED

32-41-87 Page 10009

Jun 30/10
This document is subject to the controls and restrictions on the first page.
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

AIRLINE USAGE UNITS

FIG.-ITEM PART NUMBER PART NOMENCLATURE FROM PER
NUMBER 1234567 TO ASSY

1 -85B AN960XC10L ..Washer, Flat 12

(OPT to Item 85A)

90A 551-1 ..Pad, Back Plate 12

95A 93-1037 ..Plate, Back 75A 1

-95B 93-952 ..Plate, Back 75B 1

(OPT to Item 95A)

100A 378-55 .Shield Assembly, Heat 1

105A 537-68 .Heat Sink 1

-105B 537-67 .Heat Sink 1

(OPT to Item 105A)

110A MS24665-134 .Pin, Cotter 2

(Part can be cadmium plated)

115A 20-520 .Pin, Wear Indicator 2

120A 95-569 .Adapter 2

-125A 294-9-1 .Plate Assembly, Thrust 1

130A 115-423 ..Insulator 14

135A WS175PAS17 ..Ring, Retaining 14

(True P/N is WS-175-PA-S17)
(Refer to Paragraph 1.D in the
introduction to IPL)

-135B RS175SCP ..Ring, Retaining 14

(OPT to Item 135A)

140A 294-6 ..Plate Assembly 1

145A MS21043-4 .Nut, Self-Locking 3

150A 80-741 .Washer, Flat 3

(Part can be cadmium plated)

-150B NAS1149C0432R .Washer, Flat 3

(OPT to Item 150A)

155A 43-1345 .Screw, Shoulder 3

160A 319-41 .Torque Tube 1

-160B 319-40 .Torque Tube 1

(OPT to Item 160A)

- ITEM NOT ILLUSTRATED

32-41-87
This document is subject to the controls and restrictions on the first page.
Page 10010
Jun 30/10
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

AIRLINE USAGE UNITS

FIG.-ITEM PART NUMBER PART NOMENCLATURE FROM PER
NUMBER 1234567 TO ASSY

1 165A 68-1581 .O-ring 14

170A 107-487 .Adjuster Assembly 14

(Refer to IPL Figure 2)

175A 798A .Valve, Bleeder (V27783) 2

(Part can be cadmium plated)

180A 7612 ..Cap, Valve (V27783) 1

(Part can be cadmium plated)

185A 798A-15 ..O-ring (V27783) 1

-185B NAS1611-015 ..O-ring 1

(OPT to Item 185A)

-185C NAS1612-6 ..O-ring 1

(OPT to Item 185A)

190A HTE711-59V .Fitting, Hydraulic 2

(Refer to IPL Figure 3)

195A NAS1612-6 .O-ring 2

-195B NAS1602-906 .O-ring 2

(OPT to Item 195A)

200A 50-830 .Plate, Identification 1

205A 266-236 .Piston Housing Assembly 1

(True P/N is 266-236OPT1)
(Refer to Paragraph 1.D in the introduction
to IPL)

210A 50-577 ..Plate, Identification 1

215A PLGA2180010 ..Lee Plug (V92555) 16

-215B PLGA2280010 ..Lee Plug (V92555) AR

(Service Part)

-215C PLGM0600010A ..Lee Plug (V92555) AR

(Service Part)

220A 260-843-1 ..Housing, Piston 1

(NON-PROC)

- ITEM NOT ILLUSTRATED

32-41-87 Page 10011

Jun 30/10
This document is subject to the controls and restrictions on the first page.
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

115

70
65
95
85
80
75
45
90 10
40 15
25
30

20
100

105

110

Adjuster Assembly
Figure 2/GRAPHIC 32-41-87-991-1002-A01

32-41-87 Page 10012

Jun 30/10
This document is subject to the controls and restrictions on the first page.
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

AIRLINE USAGE UNITS

FIG.-ITEM PART NUMBER PART NOMENCLATURE FROM PER
NUMBER 1234567 TO ASSY

2 -1A 107-487 Adjuster Assembly RF

5A 549-69 .Ring, Backup 1

10A 245-238 .Ring, Snap 1

15A 55-140 .Cover 1

20A 50-615 .Plate, Instruction 1

25A FN12M02 .Nut, Self-Locking 1

(Part can be cadmium plated)

30A 130-17 .Ball 1

35A 45-295 .Tube, Adjuster 1

40A 20-739 .Pin, Adjuster 1

45A 56-973 .Retainer, Pin 1

(Part can be cadmium plated)

-45B 56-971 .Retainer, Pin 1

(Part can be cadmium plated)
(OPT to Item 45A)

50A 54-620 .Sleeve 1

55A S33865-14W10 .Ring, Scraper 1

60A 68-1449 .O-ring 1

65A 68-1582 .O-ring 1

70A 549-61 .Ring, Backup 1

75A N5000-100 .Ring, Retaining 1

(Part can be cadmium plated)

-75B MS16625-3100 .Ring, Retaining 1

(OPT to Item 75A)

80A 56-842 .Retainer, Seal 1

85A 68-1519 .O-ring 1

-85B 68-1580 .O-ring 1

(OPT to Item 85A)

90A 549-18 .Ring, Backup 2

95A 26-395 .Bushing 1

- ITEM NOT ILLUSTRATED

32-41-87 Page 10013

Jun 30/10
This document is subject to the controls and restrictions on the first page.
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

AIRLINE USAGE UNITS

FIG.-ITEM PART NUMBER PART NOMENCLATURE FROM PER
NUMBER 1234567 TO ASSY

2 100A MS16625-4112 .Ring, Retaining 1

105A 113-336 .Guide, Spring 1

110A 40-676 .Spring 1

115A 74-970 .Piston 1

- ITEM NOT ILLUSTRATED

32-41-87
This document is subject to the controls and restrictions on the first page.
Page 10014
Jun 30/10
INTENTIONALLY BLANK
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

15
35

Hydraulic Fitting
Figure 3/GRAPHIC 32-41-87-991-1003-A01

32-41-87 Page 10016

Jun 30/10
This document is subject to the controls and restrictions on the first page.
GOODRICH CORPORATION
COMPONENT MAINTENANCE MANUAL
PART No. 2-1684

AIRLINE USAGE UNITS

FIG.-ITEM PART NUMBER PART NOMENCLATURE FROM PER
NUMBER 1234567 TO ASSY

3 -1A HTE711-59V Fitting, Hydraulic* RF

5A HTE717V .Cap, Protector* 1

10A HTE760-1V3 .Nipple* 1

(True P/N is HTE760-1V-3)

15A HTE7300E3-015 .O-ring* 1

(True P/N is HTE7300-E3-015)
(Refer to Paragraph 1.D in the introduction
to IPL)

-15B HTE7300E8-015 .O-ring* 1

(OPT to Item 15A)
(True P/N is HTE7300-E8-015)
(Refer to Paragraph 1.D in the introduction
to IPL)

20A HTE1001V7 .Spring* 1

(True P/N is HTE1001-V7)
(Refer to Paragraph 1.D in the introduction
to IPL)

25A HTE761V8 .Nipple, Valve* 1

(True P/N is HTE761-V8)
(Refer to Paragraph 1.D in the introduction
to IPL)

30A HTE7300E3-012 .O-ring* 1

(True P/N is HTE7300-E3-012)
(Refer to Paragraph 1.D in the introduction
to IPL)

-30B HTE7300E8-012 .O-ring* 1

(OPT to Item 30A)
(True P/N is HTE7300-E8-012)
(Refer to Paragraph 1.D in the introduction
to IPL)

35A HTE762-52V8 .Nipple, End* 1

(True P/N is HTE762-52-V8)
(Refer to Paragraph 1.D in the introduction
to IPL)

- ITEM NOT ILLUSTRATED

* Refer to page 10004 for the HTE parts vendor
32-41-87 Page 10017
Jun 30/10
This document is subject to the controls and restrictions on the first page.
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