EMAIL: jbaeza@redwings.

aero
LETTER OF TRANSMITTAL
FOR
PERMANENT REVISION NO. 10
TO
COMPONENT MAINTENANCE MANUAL
32-43-26

HYDRAULIC PLATE BRAKE P/N AHA1897

AIRCRAFT APPLICABILITY: HAWKER 125-800, 125-800XP, 750, 850XP, 900XP

ISSUED BY
MEGGITT AIRCRAFT BRAKING SYSTEMS
HOLBROOK LANE, COVENTRY CV6 4AA, ENGLAND.
COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS

1. Revision Highlights

A. Updated hydraulic fluid specification.

B. Updated the Testing and Fault Isolation page block.

C. Updated the Disassembly page block.

D. Deleted the Hydrocarbon cleaning fluid specification Evolve (Class II).

E. Replaced the S2 Primer with Primer IP-2066.

F. Updated Repair No. 7, Repair to the Bleed Screw Hole of the Cylinder Block.

G. Updated Repair No. 9, Replace the Insulator on a Piston.

H. Updated the Special tools, Fixtures and Equipment page block.

I. Minor editorial changes.

MC JETS, S.A. DE C.V.

CO: 9612

SEE EXPORT COMPLIANCE PARAGRAPH REVERSE SIDE.

 EMAIL: jbaeza@redwings.aero
EXPORT COMPLIANCE
These commodities, technology or software were exported from the United States in accordance with the Export
Administration Regulations. Diversion contrary to U.S. law is prohibited.

MC JETS, S.A. DE C.V.

CO: 9612
 EMAIL: jbaeza@redwings.aero
2. Revision Procedure
A. Remove and discard the specified pages from Meggitt Aircraft Braking Systems
component maintenance manual 32-43-26 and insert the new and revised pages
supplied:

Pages to be Removed and Discarded New and Revised Pages

Title Page - Title Page -

List of Effective Pages Page 1 and 2 List of Effective Pages Page 1 and 2

Table of Contents Pages 1 thru 4 Table of Contents Pages 1 thru 4

Description and Page 5 and 6 Description and Page 5 and 6

Operation Operation

Testing and Fault Pages 101 thru 104 Testing and Fault Pages 101 thru 104
Isolation Isolation

Disassembly Page 303 and 304 Disassembly Page 303 and 304

Cleaning Pages 401 thru 404 Cleaning Pages 401 thru 404

Repair General Pages 601 thru 604 Repair General Pages 601 thru 604

Repair No. 3 Page 601 and 602 Repair No. 3 Page 601 and 602

Repair No. 4 Pages 601 thru 604 Repair No. 4 Pages 601 thru 604

Repair No. 5 Page 601 and 602 Repair No. 5 Page 601 and 602

Repair No. 6 Pages 601 thru 604 Repair No. 6 Pages 601 thru 604

Repair No. 7 Pages 601 thru 604 Repair No. 7 Pages 601 thru 604

Repair No. 9 Pages 601 thru 604 Repair No. 9 Pages 601 thru 606

Assembly (Including Page 701 and 702 Assembly (Including Page 701 and 702
Storage) Storage)

Special Tools, Fixtures Page 901 and 902 Special Tools, Page 901 and 902
and Equipment Fixtures and
Equipment
MC JETS, S.A. DE C.V.
Illustrated Parts List Page 1005 and 1006 Illustrated Parts List Page 1005 and 1006
CO: 9612
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 EMAIL: jbaeza@redwings.aero
B. Make the necessary entry in the record of permanent revisions of component
maintenance manual 32-43-26 to certify the incorporation of this revision.
C. File this letter of transmittal.

D. This revision contains no modification information that revises the TSO configuration
and therefore does not necessitate EASA concurrence with respect to the original TSO
qualifications.

Signed:
G Percival
Chief Airworthiness Engineer
Date: May 12/14

MC JETS, S.A. DE C.V.

CO: 9612
CO: 9612 MC JETS, S.A. DE C.V. EMAIL: jbaeza@redwings.aero
 EMAIL: jbaeza@redwings.aero
LETTER OF TRANSMITTAL
FOR
PERMANENT REVISION NO. 9
TO
COMPONENT MAINTENANCE MANUAL
32-43-26

HYDRAULIC PLATE BRAKE P/N AHA1897

AIRCRAFT APPLICABILITY: HAWKER 125-800, 125-800XP, 750, 850XP, 900XP

ISSUED BY
MEGGITT AIRCRAFT BRAKING SYSTEMS
HOLBROOK LANE, COVENTRY CV6 4AA, ENGLAND.
COPYRIGHT  2012 MEGGITT AIRCRAFT BRAKING SYSTEMS

1. Revision Highlights

A. The temporary revision TR32-02 has been incorporated.

B. Updated MIL specification MIL-C-5541 to MIL-DTL-5541.

C. Replaced carborundum cloth with Norton R222 J weight P100 cloth.

D. Revised Repair No. 8 for Repair of protective paint finish.

E. Minor editorial changes.

2. Revision Procedure
A. Remove and discard the specified pages from Meggitt Aircraft Braking Systems
component maintenance manual 32-43-26 and insert the new and revised pages
supplied:

Pages to be Removed and Discarded New and Revised Pages

Title Page - Title Page -

List of Effective Pages Page 1 and 2 List of Effective Pages Page 1 and 2 MC JETS, S.A. DE C.V.

Table of Contents Page 3 and 4 Table of Contents Page 3 and 4

Introduction Page 1 and 2 Introduction Pages 1 thru 4

Testing and Fault Page 101 and 102 Testing and Fault Page 101 and 102
Isolation Isolation

Continued . . .
CO: 9612
 EMAIL: jbaeza@redwings.aero
Pages to be Removed and Discarded New and Revised Pages

Disassembly Page 303 and 304 Disassembly Page 303 and 304

Cleaning Pages 401 thru 404 Cleaning Pages 401 thru 404

Check Page 501 thru 504, Check Page 501 thru 504,
Page 507 and 508 Page 507 and 508

Repair General Pages 601 thru 604 Repair General Pages 601 thru 604

Repair No. 3 Page 601 and 602 Repair No. 3 Page 601 and 602

Repair No. 4 Pages 601 thru 604 Repair No. 4 Pages 601 thru 604

Repair No. 5 Page 601 and 602 Repair No. 5 Page 601 and 602

Repair No. 7 Page 601 and 602 Repair No. 7 Page 601 and 602

Repair No. 8 Page 601 and 602 Repair No. 8 Pages 601 thru 608

- - Repair No. 9 Pages 601 thru 604

Assembly (Including Page 705 and 706 Assembly (Including Page 705 and 706
Storage) Storage)

Illustrated Parts List Page 1003 and 1004, Illustrated Parts List Page 1003 and 1004,
Page 1007 and 1008 Page 1007 and 1008

B. Make the necessary entry in the record of permanent revisions of component

maintenance manual 32-43-26 to certify the incorporation of this revision.
C. Remove and discard temporary revision TR32-02.

D. Make the necessary entry in the record of temporary revisions of component

maintenance manual 32-43-26 to certify the removal of the TR32-02.

E. File this letter of transmittal.

F. This revision contains no modification information that revises the TSO configuration
and therefore does not necessitate EASA concurrence with respect to the original TSO
qualifications.

MC JETS, S.A. DE C.V.

Signed:
G Percival
Chief Airworthiness Engineer
Date: Nov 13/12
CO: 9612
 EMAIL: jbaeza@redwings.aero
LETTER OF TRANSMITTAL
FOR
PERMANENT REVISION NO. 8
TO
COMPONENT MAINTENANCE MANUAL
32-43-26

HYDRAULIC PLATE BRAKE P/N AHA1897

AIRCRAFT APPLICABILITY: HAWKER 125-800, 125-800XP, 750, 850XP, 900XP

ISSUED BY
MEGGITT AIRCRAFT BRAKING SYSTEMS
HOLBROOK LANE, COVENTRY CV6 4AA, ENGLAND.
COPYRIGHT ” 2009 MEGGITT AIRCRAFT BRAKING SYSTEMS

1. Revision Highlights

A. Replaced Title page that shows and satisfies the new MABS branding.

B. Revised Service Bulletin/Service Newsletter List to include all applicable Modifications.

C. Revised weight details from estimated to maximum (IAR144) (Ref. Description and
Operation).

D. Revised hydraulic fluid Specification ‘MIL-H-5606’ to ‘MIL-PRF-87257’, ‘MIL-H-83282’ to

‘MIL-PRF-83282’ and added ‘OM15’ (ECR2694) (Ref. Description and Operation,
Testing and Fault Isolation, Cleaning and Assembly (Including Storage)).

E. Revised anti-seize grease Specification ‘SAE AMS2518’ as primary use (Ref. Assembly
(Including Storage)).

F. Revised the Specification ‘Loctite 610’ to ‘Loctite 601’ (ECR3503) (Ref. Repair General).

G. Revised Spring Check Data to incorporate the details of TR32-01 (Ref. Fits and
Clearances).

H. Revised vendor code list to show correct company name and address for cage codes MC JETS, S.A. DE C.V.
K1037, 80205 and K7766 (Ref. Illustrated Parts List).

I. Revised item 2-391 and 2-392 (Assembly drawing), added item 2-540 (ECR2577) and
added vendor codes in nomenclature (Ref. Illustrated Parts List).
CO: 9612
 EMAIL: jbaeza@redwings.aero
2. Revision Procedure

A. Remove and discard the specified pages from Meggitt Aircraft Braking Systems
component maintenance manual 32-43-26 and insert the new and revised pages
supplied:

Pages to be Removed and Discarded New and Revised Pages

Title page - Title page -

Service Bulletin List Page 1/2 Service Bulletin/Service Page 1/2

Newsletter List

List of Effective Pages Page 1 and 2 List of Effective Pages Page 1 and 2

Table of Contents Pages 1 thru Table of Contents Pages 1 thru

4 4

Description and Operation Page 5 and 6 Description and Operation Page 5 and 6

Testing and Fault Isolation Page 101 and Testing and Fault Isolation Page 101 and
102 102

Cleaning Page 401 and Cleaning Page 401 and

402 402

Repair General Page 601 and Repair General Page 601 and
602 602

Assembly (Including Storage) Page 701 and Assembly (Including Storage) Page 701 and
702 702

Fits and Clearances Page 801 and Fits and Clearances Page 801 and
802 802

Illustrated Parts List Page 1003 Illustrated Parts List Page 1003
and 1004, and 1004,
Pages 1007 Pages 1007
thru 1010 thru 1010

B. Make the necessary entry in the record of permanent revisions of component

MC JETS, S.A. DE C.V.
maintenance manual 32-43-26 to certify the incorporation of this revision.

C. Remove and discard temporary revision 32-01 (Fits and Clearances) and make the
necessary entry on the record of temporary revisions page.
CO: 9612
 EMAIL: jbaeza@redwings.aero
D. File this letter of transmittal.

E. This revision contains no modification information that revises the TSO configuration
and therefore does not necessitate EASA concurrence with respect to the original TSO
qualifications.

Signed:
G Percival
Chief Airworthiness Engineer
Date: Jul 23/09

MC JETS, S.A. DE C.V.

CO: 9612
CO: 9612 MC JETS, S.A. DE C.V. EMAIL: jbaeza@redwings.aero
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
WITH ILLUSTRATED PARTS LIST
For
HYDRAULIC PLATE BRAKE
PART No. AHA1897

STATEMENT OF CERTIFICATION
The technical content of this AP-2119 is approved under the authority of Meggitt Aircraft
Braking Systems ADOA AP156.

MC JETS, S.A. DE C.V.

All Rights Reserved

Copyright © 2014
Meggitt Aircraft Braking Systems
This document is the property of Meggitt Aircraft Braking Systems and shall not be copied or used, either in whole or part, for any
purpose other than that for which it is supplied, without the express written authority of Meggitt Aircraft Braking Systems.
CO: 9612

PUB. NO: AP-2119 32-43-26 Rev 10, May 12/14

CO: 9612 MC JETS, S.A. DE C.V. EMAIL: jbaeza@redwings.aero
 EMAIL: jbaeza@redwings.aero
1 thru 6 INCORPORATED
7 INCORPORATED BY DUNLOP
8 INCORPORATED BY MABS
9 INCORPORATED BY MABS

10 INCORPORATED BY MABS

MC JETS, S.A. DE C.V.

CO: 9612
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 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
RECORD OF TEMPORARY REVISIONS

Inserted Removed
Temporary Issue
Rev. No. Date Page No.
Date By Date By

32-01 Jun 10/08 Incorporated by MABS 801

32-02 Jul 15/09 Jul 15/09 MABS Nov 13/12 MABS 601

MC JETS, S.A. DE C.V.

Record of Temporary Revisions

Page 1/2 Blank
32-43-26
CO: 9612

Rev 7, Sep 21/07

COPYRIGHT ” 2007 DUNLOP AEROSPACE LIMITED

CO: 9612 MC JETS, S.A. DE C.V. EMAIL: jbaeza@redwings.aero
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

SERVICE BULLETIN/SERVICE NEWSLETTER LIST

Service Incorporated in
Unit MOD State
Bulletin/ Manual
Part Modification No. or
Newsletter
No. New Part No. Rev. Date
No.

- AHA1897 M1822 1 I.Issue June10/91

- AHA1897 AMDT37402 1A I.Issue June10/91
- AHA1897 AMDT37763 1B 1 Jun 19/98
- AHA1897 AMDT37863 1C 1 Jun 19/98
- AHA1897 MCLB30006 1D 1 Jun 19/98
- AHA1897 MCLA21368 1E 7 Sep 21/07
- AHA1897 MCLB30470 1F 7 Sep 21/07
- AHA1897 ECR2694 1G 8 Jul 23/09
- AHA1897 IAR144 2 8 Jul 23/09

MC JETS, S.A. DE C.V.

NOTES: 1. I.Issue = Initial issue.

2. The numeric MOD state changes are recorded on the unit. The alpha changes,
which relate to minor modifications, are not recorded on the unit.
Service Bulletin List
Page 1/2 Blank
32-43-26
CO: 9612

Rev 8, Jul 23/09

COPYRIGHT ” 2009 MEGGITT AIRCRAFT BRAKING SYSTEMS
CO: 9612 MC JETS, S.A. DE C.V. EMAIL: jbaeza@redwings.aero
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
LIST OF EFFECTIVE PAGES
SUBJECT PAGE DATE SUBJECT PAGE DATE
Title Page - May 12/14 Check 501 Nov 13/12
502 Nov 13/12
Record of Permanent 1 June 10/91 503 Nov 13/12
Revisions 2 Blank 504 Jun 19/98
505 June 10/91
Record of Temporary 1 Sep 21/07 506 June 10/91
Revisions 2 Blank 507 Nov 13/12
508 Dec 11/03
Service Bulletin 1 Jul 23/09
List 2 Blank Repair General 601 Dec 11/03
602 May 12/14
List of Effective 1 May 12/14 603 May 12/14
Pages 2 May 12/14 604 Blank

Table of Contents 1 May 12/14 Repair No. 1 601 Jun 19/98

2 May 12/14 602 Jul 5/99
3 Nov 13/12 603 Jul 5/99
4 May 12/14 604 Jun 19/98
605 Aug 9/99
Introduction 1 Nov 13/12 606 Blank
2 Nov 13/12
3 Nov 13/12 Repair No. 2 601 June 10/91
4 Blank 602 June 10/91

Description and 1 Dec 11/03 Repair No. 3 601 Nov 13/12

Operation 2 Dec 11/03 602 May 12/14
3 Dec 11/03
4 Dec 11/03 Repair No. 4 601 May 12/14
5 Dec 11/03 602 May 12/14
6 May 12/14 603 May 12/14
604 Blank
Testing and 101 May 12/14
Fault Isolation 102 May 12/14 Repair No. 5 601 May 12/14
103 May 12/14 602 May 12/14
104 May 12/14
Repair No. 6 601 May 12/14
Disassembly 301 Dec 11/03 602 May 12/14
302 Dec 11/03 603 May 12/14
303 May 12/14 604 Blank
304 May 12/14 MC JETS, S.A. DE C.V.
305 Dec 11/03 Repair No. 7 601 May 12/14
306 Blank 602 May 12/14
603 May 12/14
Cleaning 401 May 12/14 604 May 12/14
402 May 12/14 605 Sep 21/07
403 May 12/14 606 Blank
404 Blank

List of Effective Pages

Page 1
32-43-26
CO: 9612

Rev 10, May 12/14

COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
SUBJECT PAGE DATE
Repair No. 8 601 Nov 13/12
602 Nov 13/12
603 Nov 13/12
604 Nov 13/12
605 Nov 13/12
606 Nov 13/12
607 Nov 13/12
608 Nov 13/12

Repair No. 9 601 May 12/14

602 May 12/14
603 May 12/14
604 May 12/14
605 May 12/14
606 Blank

Assembly 701 May 12/14

(Including 702 May 12/14
Storage) 703 Jun 19/98
704 Jun 19/98
705 Nov 13/12
706 Jun 19/98

Fits and 801 Jul 23/09

Clearances 802 2000/11/03

Special Tools, 901 May 12/14

Fixtures and 902 May 12/14
Equipment 903 Sep 21/07
904 Sep 21/07
Illustrated 1001 Dec 11/03
Parts List 1002 Dec 11/03
1003 Nov 13/12
1004 Nov 13/12
1005 Dec 11/03
1006 May 12/14
1007 Nov 13/12
1008 Nov 13/12
1009 Jul 23/09
1010 Jul 23/09
MC JETS, S.A. DE C.V.

List of Effective Pages

Page 2
32-43-26
CO: 9612

Rev 10, May 12/14

COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
TABLE OF CONTENTS
PAGE

DESCRIPTION AND OPERATION

Description 1
General
Torque Tube
Cylinder Block Assembly
Cylinder Liner Assembly
Heat Pack Assembly
Wear Indicator

Operation 5
General
Automatic Adjustment
Leading Particulars 6

TESTING AND FAULT ISOLATION

Special Tools, Equipment and Materials 101
Special Tools
Equipment
Materials
General 101
Specified Tests
References

Acceptance Tests and Bench/Shop Tests 102

Acceptance Tests
Bench/Shop Tests

Test Data 104

Fault Isolation 104

DISASSEMBLY
Special Tools 301

General 301
MC JETS, S.A. DE C.V.
Maintenance Policy
Maintenance Practices
References

Table of Contents
Page 1
32-43-26
CO: 9612

Rev 10, May 12/14

COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
PAGE

Disassembly Procedure 304

Brake
Cylinder Liner Assembly
Wear Indicator Pin

CLEANING
Materials 401

Cleaning Procedures 402

Heat Pack Components
Cylinder Block Assembly
Cylinder Liner Assembly Components
Other Metal Components
CHECK
Special Tools and Materials 501
Special Tools
Materials
General 501
Numerical equivalents
Check Procedures 501
Heat Pack
Cylinder Assembly
Cylinder Block and Torque Tube
REPAIR

Special Tools, Equipment and Materials 601

Special Tools
Equipment
Materials
List of Item Suppliers and Addresses 602

List of Repairs 603

MC JETS, S.A. DE C.V.

Table of Contents
Page 2
32-43-26
CO: 9612

Rev 10, May 12/14

COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

PAGE

Repair No. 1 – Repair of Thrust and Pressure Plate Assemblies R1-601

Repair No. 2 – Reclaim of Fully Worn Double Stator Assemblies R2-601

Repair No. 3 - Reclaim of Cracked Stator Plates – RP678 R3-601

Repair No. 4 – Repair of Damage to the Cylinder Block Assembly R4-601

Repair No. 5 – Repair of Oversize Pad Rivet Holes in Pressure Plate – RP1197 R5-601
Repair No. 6 – Repair of Worn or Damaged Torque Tube Tennons (RP1040) R6-601

Repair No. 7 – Repair to the Bleed Screw Hole of the Cylinder Block R7-601

Repair No. 8 – Repair of Protective Paint Finish on the Cylinder Block R8-601
Repair No. 9 – Replace the Insulator on a Piston (P/N AH088411) R9-601

ASSEMBLY (INCLUDING STORAGE)

Special Tools and Materials 701

Special Tools
Materials
General 702

Assembly Procedure 702

Storage After Assembly 706

FITS AND CLEARANCES

Heat Pack Data 801

Torque Tube Data 801

Spring Check Data 801

Assembly Data 802

Torque Loading 802

SPECIAL TOOLS, FIXTURES AND EQUIPMENT MC JETS, S.A. DE C.V.

Special Tools and Equipments 901
ILLUSTRATED PARTS LIST INTRODUCTION

Purpose 1001

To Use this Section 1001

Table of Contents
Page 3
32-43-26
CO: 9612

Rev 9, Nov 13/12

COPYRIGHT  2012 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
PAGE

Figure and Item Column

Part Number Column
Airline Part Number Column
Nomenclature Column
Effectivity Column
Units per Assembly Column

Vendor Code List 1004

Color Coding of Rotor Segments 1005

ILLUSTRATIONS
FIGURE TITLE PAGE
1 Brake Unit - Sectional View 2
2 Cylinder Liner Assembly 3
3 Wear Indicator 5
101 Typical Test Rig 102
301 Brake Unit - Exploded View 303
302 Piston Extraction and Disassembly 305
501 Typical Serviceable and Unserviceable Brake Pads 503
502 Cracks in Typical Rotor Segments 505
503 Rotor Shrinkage Gauge 507
R1-601 Riveting Tool Set R1-604
R3-601 Stator Plate Machining Details R3-601
R5-601 Machining and Fitting Details R5-601
R6-601 Machined Dimensions of a Repaired Torque Tube R6-602
R6-602 Installation of a Tenon Sleeve on a Torque Tube R6-603
R7-601 Dimenstions of the Machined and Tapped Hole R7-604
R7-602 Sleeve and O-ring Seal Installation R7-605
R9-601 Maximum Length of Piston Assembly R9-605
701 Cylinder Liner Assembly and Load Checking 704
IPL Figure 1 Jig-saw Segment and Table 1005
IPL Figure 2 Brake Unit - Exploded View 1006

MC JETS, S.A. DE C.V.

Table of Contents
Page 4
32-43-26
CO: 9612

Rev 10, May 12/14

COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
INTRODUCTION

This manual is written according to Air Transport Association Specification No. 100 for the overhaul
and/or maintenance of the Meggitt Aircraft Braking Systems (MABS) (MABS® is the registered
trademark of Meggitt Aircraft Braking Systems) assembly(ies) included. THIS MANUAL IS
APPLICABLE ONLY FOR THE OVERHAUL OF THE INCLUDED MABS PRODUCT(S) WITH
ONLY MABS PRODUCED OR APPROVED PARTS AND APPROVED PROCEDURES. THE USE
OF UNAPPROVED PARTS OR THE OMISSION OR ALTERATION OF APPROVED
PROCEDURES NEGATES THE VALIDITY OF THIS MANUAL.

The person or facility that uses unapproved procedures or omits recommended procedures to do
an overhaul or maintenance to MABS products may not rely on this manual, must do so at their
own risk and must assume product liability. All torque values and specific limits apply only to MABS
approved parts/products and must be obeyed. Any alternative procedures, limits, or materials (if
consented to in writing by MABS) must not decrease the performance of the assembly.

The Illustrated Parts List of this manual lists and illustrates only the approved parts required to do
maintenance to the assemblies in this manual. The use of unapproved parts in these assemblies
may change the product's performance capability and will nullify the product warranty. The person
or facility that puts unapproved parts in the assemblies may not utilize this manual, must do so at
their own risk and must assume product liability.

All dimensions and other values are in English units followed by the SI (International System) units.
Illustration dimensions are in inches with millimeter conversions in parentheses. Dimensions of
standard tools or parts are in English units where there are no equivalent metric tools or parts.
Illustrations are for reference only and are not to scale.

Meggitt Aircraft Braking Systems represents that the information contained in this manual is valid
only for use with MABS approved parts and procedures and was current at the time of publication
and verified by comparison to engineering documentation.

The user should make sure that this is the most recent publication before overhaul or maintenance
is performed. A dealer, distributor or Customer Support Department can tell the user if this is the
most recent manual. You may make direct inquires to the Distributor Representative-Marketing,
Meggitt Aircraft Braking Systems, Holbrook Lane, Coventry – CV6 4AA, United Kingdom or to the
Technical Publication Department on e-mail at pubs-support@meggitt.com.

If this manual and the aircraft maintenance manual do not agree on the aircraft interface
connections, use the aircraft maintenance manual. This manual may give component functions that
may or may not be used when installed on the aircraft.
MC JETS, S.A. DE C.V.

Introduction
Page 1
32-43-26
CO: 9612

Rev 9, Nov 13/12

COPYRIGHT  2012 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
NOTICE

MEGGITT AIRCRAFT BRAKING SYSTEMS (MABS) ASSUMES NO CONTRACTUAL,

WARRANTY, PRODUCT LIABILITY OR OTHER OBLIGATION FOR ANY SUBSTITUTION OF OR
ALTERATION TO ANY PART CONTAINED IN ANY MABS WHEEL OR BRAKE ASSEMBLY
INCLUDING ACCESSORIES NOT SPECIFICALLY AUTHORIZED BY MABS OR FOR ANY
OVERHAUL OR MAINTENANCE NOT PERFORMED IN ACCORDANCE WITH MABS
APPROVED PROCEDURES.

DATA RIGHTS

The cost for this manual includes printing and shipping costs only and does not include purchase of
the data or design. It does not give the purchaser any rights or patent to print or make parts from
this data.

SAFETY SUMMARY

Obey all manufacturer's Warnings and Cautions for all materials specified in this manual. In this
manual, Warnings and Cautions come before the procedure to which they apply. Failure to obey a
Warning may cause personal injury. Failure to obey a Caution may cause damage to equipment or
components. Wear protective clothing approved for the materials and tools being used.

CONFORMANCE NOTICE

This assembly for commercial transport usage has a "TSO" marking which identifies it as having
been fully laboratory tested and qualified to the applicable European Aviation Safety Agency
(EASA) regulations.

Although this commercial transport category assembly may have been tested and qualified to the
specification requirements of the applicable airframe manufacturer and certified on the applicable
aircraft, it is the responsibility of the installer to determine that the assembly maintained in
accordance with this manual is approved for installation.

Any replacement of or change to any part, manufacturing process or material that affects or may
affect conformance to TSO requirements and/or airframe manufacturer's specifications is not
permitted after certification without applicable requalification of this assembly and resubmittal of this
test data to the EASA and/or airframe manufacturer for approval.

The use of parts manufactured by sources other than MABS and not approved by MABS in any
assembly that has the MABS name and TSO marking will relieve MABS of any warranty obligation
relating to the assembly upon which the unapproved part has been installed and will relieve MABS
of all product liability responsibility for that assembly or any other assemblies on the aircraft and the MC JETS, S.A. DE C.V.
aircraft it may be used on.

Introduction
Page 2
32-43-26
CO: 9612

Rev 9, Nov 13/12

COPYRIGHT  2012 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
The EASA regulations subject Meggitt Aircraft Braking Systems, the airframe manufacturer and the
operator, to constant surveillance to assure that proper quality assurance, material and processing
controls are maintained in order to provide MABS replacement parts that are the same quality as
the parts originally certified in this assembly.

ON-CONDITION MAINTENANCE

Each operator must schedule maintenance based on the condition of his equipment. Meggitt
Aircraft Braking Systems recommends that on-condition maintenance be performed.

ATA Common Support Data Dictionary (CSDD) defines on-condition maintenance as

follows:

A primary maintenance process having repetitive inspections or tests to determine the condition of
units, systems or portions of structure with regard to continued serviceability (corrective action is
taken when required by item condition).

MABS CUSTOMER SUPPORT LOCATIONS

To locate your dedicated field customer support representative, go to www.meggitt-mabs.com and

click on the Field support link.

MC JETS, S.A. DE C.V.

Introduction
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

DESCRIPTION AND OPERATION

1 Description

A. General (Figure 1)

(1) Hydraulic pressure operates this brake unit. It is a plate-type

brake unit with a cylinder block assembly of five cylinder liner
assemblies and a heat pack assembly.

(2) Each cylinder liner assembly has a piston assembly and other
internal components for automatic adjustment. Automatic adjustment
keeps a set clearance during wear of the heat pack assembly. This
makes sure that no more than a constant quantity of fluid is
necessary to move the brake during operation.

(3) The heat pack assembly has segmented (jigsaw type) rotor assemblies
that are located between pressure, double stator and thrust plate
assemblies each with inorganic pads.

(4) The brake unit can be used on the right or left undercarriage.

B. Torque Tube

(1) Tenons machined at equal distances around the outside diameter let
the torque tube engage with slots of the pressure stator, double
stators and thrust stator.

(2) A locating collar is riveted to the cylinder block end of the torque
tube. This engages and extends through the cylinder block assembly.

C. Cylinder Block Assembly

(1) Fluid ways in the cylinder block assembly connect the cylinder liner
assemblies, bleed valve assemblies and shuttle valve (when
installed).

(2) A ring nut is installed on the locating collar of the torque tube to
attach the cylinder block assembly to the torque tube.

(3) Two bolts and washers attach two indicator brackets to the outer
face of the cylinder block assembly.
MC JETS, S.A. DE C.V.
D. Cylinder Liner Assembly

(1) A piston assembly is installed in the internal diameter of the

cylinder liner. A back-up ring and a sealing ring, also installed,
make a fluid-tight seal.


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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

MC JETS, S.A. DE C.V.

Brake Unit - Sectional View

Figure 1


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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

Cylinder Liner Assemby

Figure 2

(2) For automatic adjustment a spacer, guide, friction bush and spring
are all installed in the piston assembly. A retaining washer and
circlip holds them all in position. A retraction pin is installed
into the piston assembly, through the cylinder liner, retaining
washer, guide and friction bush. The friction bush holds the
retraction pin in its automatically adjusted position.

(3) Installed in the end of each piston is a heat insulator.

E. Heat Pack Assembly

(1) Components of the heat pack assembly are:

- Pressure plate assembly
- Segmented rotor assembly (quantity 3)
- Double stator assembly (quantity 2)
- Thrust plate assembly
MC JETS, S.A. DE C.V.
(2) Pressure Plate Assembly

(a) The internal diameter of the pressure plate assembly has tenon
slots to engage with the tenons of the torque tube.


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HYDRAULIC PLATE BRAKE, PART NO. AHA1897

(b) The pressure plate assembly is installed (on the torque tube)
with pads riveted to its inner face. The outer face is
directly against the heat insulators of the cylinder liner
assemblies.

(c) Rivets attach two indicator pin retainers to the outer face of
the pressure plate assembly.

(3) Segmented Rotor Assembly

(a) Segmented rotor assemblies (each of 6 segments) are installed

between the:
- Pressure plate assembly and double stator assembly
- Double stators
- Double stator and thrust plate assembly.

(b) The outer edge of each rotor segment includes a tenon to engage
with a related drive bar of the main wheel.

(4) Double Stator

(a) The internal diameter of each double stator assembly has tenon
slots to engage with the tenons of the torque tube.

(b) The double stators are installed, with pads riveted to each
face, between the three segmented rotor assemblies on the
torque tube.

(5) Thrust Plate Assembly

(a) Installed last (on the torque tube), the thrust plate assembly
safties all the other heat pack components. The thrust plate
assembly is installed with pads riveted to its inner face.

(b) The internal diameter of the thrust plate assembly has bolt
holes. Bolts attach the thrust plate assembly to the torque
tube assembly.

F. Wear Indicator

(1) Two indicator pins are installed, the thicker end of each is
installed in a indicator pin retainer. To safety, a split pin goes
through the indicator pin retainer and the indicator pin. The MC JETS, S.A. DE C.V.
pointed end of the indicator pin goes through an indicator bracket
of the cylinder block assembly.


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HYDRAULIC PLATE BRAKE, PART NO. AHA1897

Wear Indicator
Figure 3

(2) The distance between face B of the indicator bracket and the end
face of the wear pin, when the brake is pressurised, shows the
quantity of wear remaining in the heat pack assembly. The heat pack
assembly is fully worn when the end face of the wear pin is aligned
with face B of the indicator bracket.

2 Operation

A. General

(1) Hydraulic pressure, to operate the brake unit, transmits through an

inlet connection of the shuttle valve assembly. The shuttle valve
then operates to transmit the hydraulic pressure through the fluid-
ways of the cylinder block assembly to each cylinder liner assembly.

(2) Each piston assembly of each cylinder liner assembly puts a force on
the pressure plate assembly. This force, related to the hydraulic
pressure, pushes all stators and rotors together against the thrust
plate assembly. This gives a frictional resistance against the
rotor assemblies that are usually free to turn.

(3) Release of hydraulic pressure lets each spring (one installed in

each cylinder liner assembly) retract its piston to brake off MC JETS, S.A. DE C.V.
position.

B. Automatic Adjustment

(1) When the brake operates, movement of each piston causes each spring
to compress. Each spring compresses to the limit of clearance
between a guide shoulder and a retaining washer. This travel of the
piston is known as primary movement.


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(2) Movement more than primary movement is known as secondary movement and this
occurs when the heat pack assembly wears. Secondary movement causes each
friction bush to be pushed along its retraction pins. This automatic adjustment keeps
the correct clearance between the heat pack components. When hydraulic pressure
releases, the piston moves back only by the distance of primary movement.

3. Leading Particulars

Unit Part No. AHA1897

Fluid Specification MIL-PRF-5606 (DEF STAN 91-48)

or MIL-PRF-83282

Maximum Operating Pressure 1900 psi (131 bar)

Cylinder Block Material Aluminium Alloy

Overall Dimensions 11.03 in. x 5.187 in. (280,16 mm x 131,75 mm)

Maximum Weight 43.94 lb (19,93 kg)

NOTE: Alternative hydraulic fluid MIL-PRF-83282 has a different temperature limit. Before use,
do a check of the Aircraft Maintenance Manual that MIL-PRF-83282 is satisfactory.

MC JETS, S.A. DE C.V.

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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

TESTING AND FAULT ISOLATION

1. Special Tools, Equipments and Materials

NOTE: Equivalent alternatives can be used.

A. Special Tools

Tool List Description Remarks

Item No.

11 Torque spanner with For bleed screws

1/4 in. square drive

12 Torque spanner adapter For bleed screws

15 Adapter For testing brake unit with shuttle valve

removed

B. Equipment

(1) Pressure gauge suitable for pressures from 0 to 1900 psi (0 to 131 bar).
(2) Suitable pipelines, control valve and bleed point (Ref. Figure 101).
(3) Hydraulic test rig that can supply hydraulic fluid MIL-PRF-5606 (DEF STAN 91-48)
or MIL-PRF-83282 with a filtration standard of NAS1638 Class 7 or better.

C. Materials

(1) Hydraulic fluid, MIL-PRF-5606 (DEF STAN 91-48) or MIL-PRF-83282.

NOTE: Refer to the note in Leading Particulars for the temperature limit of
hydraulic fluid.

2. General

A. Specified Tests

(1) If it is necessary to test new or other serviceable units removed from storage, do
the Acceptance Tests.
(2) When a brake unit is removed from an aircraft complete the bench/shop tests as MC JETS, S.A. DE C.V.
the first part of fault isolation.
(3) After a brake unit is assembled (subsequent to other maintenance procedures)
complete the bench/shop tests. Find if the brake unit is fully serviceable.

B. References

(1) Refer to Test Data, para 4. For the numerical values of the letters quoted in the
following instructions.

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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
3. Acceptance Tests and Bench/Shop Tests

WARNING: THE HYDRAULIC PLATE BRAKE IS HEAVY. USE THE APPLICABLE

EQUIPMENT TO SAFELY LIFT THE HYDRAULIC PLATE BRAKE UNIT.

CAUTION: PREVENT CONTAMINATION OF HYDRAULIC FLUIDS, OILS AND GREASES

ON THE FRICTION SURFACES.

A. Acceptance Tests

(1) Remove the bolts (500), blanking plate (510) and sealing strip (520) from the inlet.
Fit the sealing washer (Part of Tool item No. 15) to test adapter (Part of
Tool Item No. 15) and secure the test adapter with bolts (Part of Tool Item No. 15)
to the inlet in the cylinder block.

(2) Put the brake unit on a clean bench, with the cylinder block at the top. Connect a
test rig (Ref. Figure 101). Apply a pressure of 100 psi (6,89 bar), open the bleed
screws to bleed the test rig and brake unit. When the fluid is free of air, torque
tighten the bleed screws to 30 lbf in. (3,39 Nm) using special tools
(Tool Item Nos. 11 and 12).

NOTE: Too much system pressure during bleeding will cause ‘froth’ and it will not
be easy to find fluid that is free of air.

Typical Test Rig

Figure 101
MC JETS, S.A. DE C.V.
(3) Pressurize the brake unit to 1900 psi (131 bar) at a frequency of 12 times per
minute. Do a check that the brake operates when pressure is applied and released.

(4) Pressurize the brake unit to 1900 psi (131 bar). Do a check that there is no leakage
over a 5 minute period.

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HYDRAULIC PLATE BRAKE, PART NO. AHA1897
(5) Decrease the pressure to 5 psi (0,34 bar). Do a check that there is no leakage over
a 15 minute period.

(6) On satisfactory completion of testing and if a new heat pack and new indicator
pins (206) are installed:
- Pressurize the brake unit to 1900 psi (131 bar) and crop each indicator
pin to 0.500 in. from face B (Ref. Figure 3).

(7) Remove the adapter assembly (Tool Item No. 15) from the inlet connection. Install
the sealing strip (520), blanking plate (510) and bolts (500) to the inlet connection.

B. Bench/Shop Tests

WARNING: THE HYDRAULIC PLATE BRAKE IS HEAVY. USE THE APPLICABLE

EQUIPMENT TO SAFELY LIFT THE HYDRAULIC PLATE BRAKE UNIT.

CAUTION: PREVENT CONTAMINATION OF HYDRAULIC FLUIDS, OILS AND

GREASES ON THE FRICTION SURFACES.

(1) Prepare and bleed the brake unit (Ref. paras A.(1) and A.(2)).

(2) Pressurize the brake unit to 1900 psi (131 bar). Make sure that the indicator pins go
through the indicator brackets. Remove the pressure and record the brake
clearance.

(3) Pressurize the brake unit to 1900 psi (131 bar) and slowly decrease the pressure to
50 psi (3,44 bar). Do a check that the adjusters cause the same brake clearance
(approximately) as recorded (Ref. step (2)). Release the brake pressure.

(4) Pressurize the brake unit to 50 psi (3,44 bar). Do a check that the rotors can be
turned by hand without too much effort.

(5) Operate the unit for some minutes at a frequency of 12 times per minute with
1900 psi (131 bar) applied. Do a check of the brake unit for leaks. Leaks are not
permitted:

(a) After a period of 5 minutes with 1900 psi (131 bar) applied.

(b) After a period of 15 minutes with 5 psi (0,34 bar) applied.

(6) Remove the pressure, remove the unit from the test rig, remove the test adapter
(Tool Item No. 15). Install the sealing strip (520), blanking plate (510) and bolts
(500) to the inlet connection. MC JETS, S.A. DE C.V.

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4. Test Data

Bleeding
Test Pressure
Pressure
Brake Part No.
A psi (bar) B psi (bar) C psi (bar) D psi (bar)

AHA1897 100 (6,89) 1900 (131) 5 (0,34) 50 (3,44)

5. Fault Isolation

NOTE: The test letters quoted in the following table refer to the Bench/Shop Tests detailed in
para 3.B.

Test Fault Cause Rectification

(2) Sluggish response of Air in hydraulic system Bleed the brake

pistons (Ref. para 3.A.(2))

(3) Adjusters fail to restore Unserviceable Disassemble and do a load

original brake retraction pins or check on retraction pins
clearance friction bushes

(4) With correct pressure Weak return springs Disassemble and do the
applied rotors cannot spring load deflection tests
be turned by hand

(5) Fluid leakage from Faulty seal on cylinder Disassemble and renew
cylinder liner assembly liner or piston faulty seal

(5) Fluid leakage from Loose bleed screw Check components for
bleed point and/or adapter or faulty looseness, re-torque as
seal necessary. If leakage
persists renew faulty seal

(5) Fluid leakage not Fractured cylinder Renew cylinder block or

attributed to previous block or leaking cylinder block plug
causes cylinder block plug

MC JETS, S.A. DE C.V.

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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

DISASSEMBLY

1. Special Tools

NOTE: 1. Alternatives can be used.

2. Use torque spanner adaptors with a ratchet handle (or T-handle)

and a square drive of the correct size.

3. Refer to Special Tools, Fixtures and Equipment for the full

description of each tool.

Tool Description Remarks

Item
No.

2 Key spanner For ring nut

3 Loading and extraction tool For disassembly of cylinder
assemblies
7 Torque spanner adapter For thrust plate attachment bolts
9 Torque spanner adapter For shuttle valve/blanking plate
attachment bolts
10 Torque spanner adapter For bleed screw adapters
12 Torque spanner adapter For bleed screws

2. General

A. Maintenance Policy

(1) The maintenance procedures in this manual relate to an on-condition

maintenance policy (the isolation of a fault to a component or
assembly and the replacement of the unserviceable item). To
maintain a brake to satisfy this policy it is necessary to know the
wear remaining length (brake pressurised) of the wear pin before
the brake is disassembled.

(2) Do not disassemble the brake unit more than is necessary for fault
isolation and removal of an unserviceable item. If full
maintenance is necessary complete all disassembly procedures before
subsequent maintenance tasks (Cleaning, Checks, Repairs and
Assembly). MC JETS, S.A. DE C.V.

B. Maintenance Practices

(1) As the component parts are disassembled put them away from tools
and equipment that can cause damage.

(2) Make sure to prevent contamination of the friction faces by fluids

and/or greases.


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30 BLEED SCREW 240 PISTON

40 ADAPTER BLEED SCREW 250 CIRCLIP
50 RING SEALING 260 RETAINING WASHER
60 BOLT 265 SHIM
65 HEAT PACK ASSEMBLY 270 SPRING
70 THRUST PLATE ASSEMBLY 280 GUIDE
80 RIVET 290 SPACER
90 PLATE RIVET 295 SHIM
100 PAD ASSEMBLY 300 FRICTION BUSH
105 PACKING PIECE 310 RETRACTION PIN
110 THRUST PLATE 320 RING SEALING
120 ROTOR SEGMENT 330 RING BACK-UP
130 DOUBLE STATOR ASSEMBLY 340 CYLINDER LINER
140 RIVET 350 RING SEALING
150 PAD ASSEMBLY 360 RING SPLIT
160 STATOR PLATE 370 LOCKING PIN
170 PRESSURE PLATE ASSEMBLY 380 RING NUT
180 RIVET 390 CYLINDER BLOCK ASSEMBLY
190 PAD ASSEMBLY 391 BOLT
195 PACKING PIECE 392 WASHER
197 INDICATOR PIN RETAINER 393 BRACKET INDICATOR
200 PRESSURE PLATE 460 TORQUE TUBE ASSEMBLY
204 PIN SPLIT 470 RIVET
206 PIN INDICATOR 480 LOCATING COLLAR
210 ClRCLIP 482 RIVET
220 CYLINDER LINER ASSEMBLY 484 FOULING PIECE
MC JETS, S.A. DE C.V.
225 PISTON ASSEMBLY 490 TORQUE TUBE
230 INSULATOR

Key to Figure 301


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MC JETS, S.A. DE C.V.

Brake Unit – Exploded View

Figure 301

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HYDRAULIC PLATE BRAKE, PART NO. AHA1897
(3) Before disassembly of the heat pack, identify the sequence position and orientation
of all its components to make sure that they can be assembled back in their original
relationship. Also identify the heat pack with its brake unit.

(4) Discard all seals removed during disassembly.

C. References

(1) Identify the item numbers in brackets (parenthesis) as those shown in Figure 301.

3. Disassembly Procedure

WARNING: THE HYDRAULIC PLATE BRAKE IS HEAVY. USE THE APPLICABLE

EQUIPMENT TO SAFELY LIFT THE HYDRAULIC PLATE BRAKE UNIT.

A. Brake

(1) Put the brake unit on a clean bench with the cylinder block assembly (390) down.
Use special tools (Tool Item Nos. 10 and 12) and remove bleed screws (30), bleed
screw adapters (40). Remove sealing rings (50).

(2) Use special tool (Tool Item No. 9) and remove the shuttle valve or blanking plate as
appropriate. Drain hydraulic fluid into an applicable container.

(3) Use special tool (Tool Item No. 7) and remove thrust plate attachment bolts (60).
Remove:
- 1 thrust plate assembly (70).
- 3 rotor segment assemblies (120).
- 2 double stator assemblies (130).
- 1 pressure plate assembly (170).

NOTE: Do not disassemble pad assemblies unless they are worn or unserviceable
(Ref. Repair).

(4) Remove circlips (210) and cylinder liner assemblies from cylinder block (390).

(5) Remove and discard split pin (360) and extract locking pin (370). Use special tool
(Tool Item No. 2) and unscrew ring nut (380) from torque tube assembly (460).

B. Cylinder Liner Assembly

(1) Install the cylinder liner assembly (220) into special tool (Tool Item No. 3)
(Ref. Figure 302, Location A). MC JETS, S.A. DE C.V.
(2) Turn the T bar of the special tool to remove piston assembly (225) from cylinder
liner (340).

(3) Install the piston assembly (225) into special tool (Tool Item No. 3)
(Ref. Figure 302, Location B).

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Piston Extraction and Disassembly

Figure 302

(4) Turn in the T bar of the special tool to compress spring (270)
sufficient to remove circlip (250).

(5) Slowly screw out the T bar of the special tool and remove retaining
washer (260), shim (265), spring (270), guide (280), spacer (290),
shims (295) and friction bush (300) from piston (240).

(6) Remove retraction pin (310), sealing ring (320), back-up ring (330)
and seals (350) from cylinder liner (340).

NOTE: Disassembly of other components is not necessary unless the MC JETS, S.A. DE C.V.
components are unserviceable.

C. Wear Indicator Pin

(1) Remove split pin (204) and indicator pin (206) from pressure plate
assembly (170).


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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

CLEANING

1. Materials

NOTES: (1) Equivalent alternatives can be used.

(2) Refer to the note in Leading Particulars for the temperature limit of hydraulic
fluid.

Description Specification Supplier

Hydraulic fluid MIL-PRF-5606 (DEF STAN 91-48) Local supply

or MIL-PRF-83282

Hydrocarbon Class III blend of hydrocarbons Local supply, or

cleaning fluid

- Lotoxane Reabrook Limited

(Class III) T/A Arrow Chemicals
Rawdon Road
Moira Swadlincote
Derbyshire DE12 6DA
United Kingdom
(Vendor code U0698)

- Multisol M56 Multisol Ltd

(Class III) Welsh House
83 Welsh Row
NANTWICH
Cheshire
CW5 5ET
United Kingdom
(Vendor code KCVF8)

Cloth, lint-free - Local supply

Disposable paper - Local supply

tissues

Brush Dry and with stiff bristles Local supply

MC JETS, S.A. DE C.V.

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2. Cleaning Procedures

A. Heat Pack Components

(1) Remove oil, grease or any other contamination with dry disposable paper tissues.

(2) Clean the heat pack components with a dry brush of stiff bristles.

B. Cylinder Block Assembly (Figure 301, item 390)

WARNING: HYDROCARBON CLEANING FLUID IS A HAZARDOUS MATERIAL.

BEFORE YOU USE IT, MAKE SURE THAT YOU KNOW THE SAFETY
PRECAUTIONS AND FIRST AID INSTRUCTIONS ON:
- THE LABEL ON THE CONTAINER IT WAS SUPPLIED IN
- ITS MATERIAL SAFETY DATA SHEET
- YOUR LOCAL SAFETY REGULATIONS.

CAUTION: DO NOT LET HYDROCARBON CLEANING FLUID OR OTHER SOLVENTS

COME INTO CONTACT WITH RUBBER COMPONENTS.

(1) Use hydrocarbon cleaning fluid to flush the internal surfaces (fluid-ways) of the
cylinder block assembly (390).

(2) Use a lint-free cloth, if necessary made moist with hydrocarbon cleaning fluid to
thoroughly clean the external surfaces of the cylinder block assembly (390).

CAUTION: REMOVE ALL CHLORINATED SOLVENT FROM INTERNAL SURFACES

AND FLUID-WAYS BEFORE ASSEMBLY. USE THE AIR BLAST PROCESS
OR OTHER EFFECTIVE METHOD. IF SOME HYDROCARBON CLEANING
FLUID OR OTHER CHLORINATED SOLVENT USED TO CLEAN THE
ITEMS OF THE BRAKE UNIT STAYS ON THE ITEMS, THEN IT CAN
COMBINE WITH VERY SMALL QUANTITIES OF WATER IN HYDRAULIC
SYSTEMS TO MAKE HYDROCHLORIC ACID.

(3) Make sure that cylinder block assembly (390) is fully dry.

WARNING: HYDRAULIC FLUID IS A HAZARDOUS MATERIAL. BEFORE YOU USE IT,

MAKE SURE THAT YOU KNOW THE SAFETY PRECAUTIONS AND FIRST
AID INSTRUCTIONS ON:
- THE LABEL ON THE CONTAINER IT WAS SUPPLIED IN
- ITS MATERIAL SAFETY DATA SHEET
- YOUR LOCAL SAFETY REGULATIONS.

(4) Flush the internal surfaces (fluid-ways) of the cylinder block assembly (390) with MC JETS, S.A. DE C.V.
clean hydraulic fluid MIL-PRF-5606 (DEF STAN 91-48) or MIL-PRF-83282.

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C. Cylinder Liner Assembly Components (Figure 301, item 220)

WARNINGS 1. HYDROCARBON CLEANING FLUID IS A HAZARDOUS MATERIAL.

BEFORE YOU USE IT, MAKE SURE THAT YOU KNOW THE
SAFETY PRECAUTIONS AND FIRST AID INSTRUCTIONS ON:
- THE LABEL ON THE CONTAINER IT WAS SUPPLIED IN
- ITS MATERIAL SAFETY DATA SHEET
- YOUR LOCAL SAFETY REGULATIONS.

2. HYDRAULIC FLUID IS A HAZARDOUS MATERIAL. BEFORE YOU

USE IT, MAKE SURE THAT YOU KNOW THE SAFETY
PRECAUTIONS AND FIRST AID INSTRUCTIONS ON:
- THE LABEL ON THE CONTAINER IT WAS SUPPLIED IN
- ITS MATERIAL SAFETY DATA SHEET
- YOUR LOCAL SAFETY REGULATIONS.

(1) Piston Assemblies (225) and Cylinder Liners (340)

(a) Use hydrocarbon cleaning fluid to clean the piston assemblies (225) and the
cylinder liners (340).

(b) Make sure that the piston assemblies (225) and cylinder liners (340) are fully
dry.

(c) Lubricate the metal surfaces of the piston assemblies (225) and cylinder
liners (340) with hydraulic fluid MIL-PRF-5606 (DEF STAN 91-48) or
MIL-PRF-83282.

(2) Clean all other cylinder liner assembly components with clean hydraulic fluid
MIL-PRF-5606 (DEF STAN 91-48) or MIL-PRF-83282.

D. Other Metal Components

WARNING: HYDROCARBON CLEANING FLUID IS A HAZARDOUS MATERIAL.

BEFORE YOU USE IT, MAKE SURE THAT YOU KNOW THE SAFETY
PRECAUTIONS AND FIRST AID INSTRUCTIONS ON:
- THE LABEL ON THE CONTAINER IT WAS SUPPLIED IN
- ITS MATERIAL SAFETY DATA SHEET
- YOUR LOCAL SAFETY REGULATIONS.

(1) Use hydrocarbon cleaning fluid to thoroughly clean all other metal components.

(2) Make sure all components are fully dry. MC JETS, S.A. DE C.V.

Page 403/404 Blank

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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
CHECK

1. Special Tools and Materials

A. Special Tools

Tool List Description Remarks

Item No.

1 Tenon wear gauge For stator and pressure plate

tenon slots

B. Materials

(1) Norton R222 J Weight P100 cloth.

2. General

A. Numerical Equivalents

(1) The numerical equivalents of the letters quoted in the check procedure are given in
a different section (Ref. Fits and Clearances).

3. Check Procedures

A. Heat Pack

(1) General

CAUTIONS: 1. A HEAT PACK WITH INDICATOR PINS FLUSH TO THE

FACE OF THE CYLINDER BLOCK ASSEMBLY IS FULLY
WORN AND UNSERVICEABLE, IT MUST BE REPLACED.

2. ALL ROTOR SEGMENTS OF A FULLY WORN HEAT PACK

MUST BE DISCARDED.

3. A HEAT PACK WITH ONLY ONE COMPONENT ASSEMBLY

FOUND TO BE UNSERVICEABLE MUST BE REPLACED.

NOTE: The pressure, thrust and stator plates assemblies of a fully worn heat pack
can be repaired (Ref. Repair) to form part of a new heat pack.
MC JETS, S.A. DE C.V.
(a) Complete steps (2) thru (3) to make sure that components of a worn heat
pack are serviceable. Reject an unserviceable heat pack or component.

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(2) Stator, Pressure and Thrust Plate Assemblies

(a) Stator plate tenon slots are subject to shrinkage in the early stages. Examine
each slot as follows:

1 Check for shrinkage. The slot width must not be less than P in.

2 Check for wear. If wear has occurred one face only, use special tool (Tool
Item No. 1) to check that the slot width is not more than Q in. If wear has
occurred on both faces because of reversal of the stator to equalize wear,
the maximum permitted width is increased to R in.

(b) Check that the clearances of the stator is not less than S in. when measured
between slots and T in. when measured to the base of the slots.

NOTE: The dimensions for stator tenon slots and bore clearances detailed
in sub-paras (a) and (b) above, apply also to the pressure plate.

(c) Check the stator plate outer diameter is not more than W in.

(d) Check the stator plate for cracks. A cracked plate or one which fails to
comply with the checks given in sub-paras (a), (b) and (c) above, makes the
heat pack unserviceable, but may be reclaimed as detailed in Repair No. 3.

(e) Check the brake pads for security of attachment. Limited looseness is
permitted providing the pad does not rock and that the projections on the
back of the pad backing plate are not disengaged from the holes in the
associated plate.

NOTE: There will be no significant loss of braking performance, if the stators

are retained in service up to the limit of permitted deterioration.

(f) Examine the pads for deterioration. At all stages of wear, surface
deterioration such as edge crumbling, cracking or crazing can be
disregarded.

(g) A condition where an area of pad material has broken clearly away to bare
the backing plate indicates a loss of the bond and makes the heat pack
unserviceable. An advanced stage of this condition is illustrated
(Ref. Figure 501, Location B).

MC JETS, S.A. DE C.V.

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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

Typical Serviceable and Unserviceable Brake Pads

Figure 501

(h) Inspect for material breakaway (Ref. Figure 501, Location A) and where it
has occurred do a test on the bond of the remaining pad material. Try to lift
with the end of a suitable tool that will avoid damage of too much leverage
(use a tool the same or almost the same rigidity and length as a pen knife).
Remove loose or crumbling pad material and estimate serviceability:

1 The total loss of pad material for a stator face must not be more than
4 in2 (2580 mm2).

MC JETS, S.A. DE C.V.

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2 The loss of material for a pad must not be more than 1.5 in2
(968 mm2).

NOTE: Total area of a pad is approx 5.33 in2 (3440 mm2).

3 Where loss of material has occurred on a pad, within the

limits of sub-para 2, surface deterioration (Ref. sub-para
(f)) of an adjacent pad is permitted but break away of pad
material (Ref. sub-paras (g) and (h)) on an adjacent pad is
not permitted.

(i) Visually examine the outer edges of the blanking plate for
fractures. No fractures permitted.

(j) Examine the pressure and thrust plate for damage, twist and
corrosion. Twist in excess of G in. makes the heat pack
unserviceable.

(k) Examine the thrust plate retaining bolts for damage and
condition of threads.

(3) Rotor Assemblies

Examine each rotor as a complete assembly as follows:

NOTE: Segments can twist and become tight after a period of

service. This condition is normal and must be disregarded.

(a) Check if width reduction of the segment tenons has occurred

because of brinelling. The minimum permitted width of the
tenon is E in. Do not file the abutment faces.

(b) Visually examine the friction faces of the segment. Two types
of defect may be found, the second sometimes being a
development of the first.

1 An illustration (Ref. Figure 502, Plate 1) shows surface

deterioration in the form of a series of very small cracks
similar to glazing cracks found in pottery. The different
areas illustrate the different ways this fault can first
develop. A limited quantity of this type of surface cracks
is permitted in central areas of the segments, for example
a segment with a similar total area of surface cracking to MC JETS, S.A. DE C.V.
that shown (Ref. Plate 1) can be regarded as serviceable
but more cracking in the areas above and below the slot can
warrant rejection. The small surface cracks in the tongue
and above the slots, shown in areas X, Y and Z (Ref.
Plate 2), are permitted if the cracks do not extend to the
edge of the segment in the general direction of P and R.

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~ DUNLOP LIAlEIT.EJD
COMPONENT MAINTENANCE MANUAL
PART NO.AHA 1897

PLATE 1

JEW

PLATE 2

Cracks in Typical Rotor Segments

Figure 502

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PART NO.AHA 1897

2 Plate 2 illustrates how the minute surface cracks shown on

Plate 1 may eventually join to form major cracks. Anyone
of the major cracksshown and major cracking of any kind
on the tongues and above and below the slot would
render the assembly unserviceable.

3 Cracks similar to those shown on Plate 2 irrespective of

whether they have developed from minor surface cracks,
or whether they are isolated, must be judged in accordance
with the following principles.

4 Cracks up to 0.375 in. long (9,525 mm) are permitted in the

central area, providing they show no tendency to join and
form major cracks and providing they cover only a limited
area of the segment.

5 Short cracks similar in magnitude to those illustrated on

Plate 2, but less than 0.375 in. long (9,525 mm) still render
the assembly unserviceable if within 0.375 in. (9,525 mm)
of a segment edge or slot.

EXAMPLES: The major cracks shown at A, C and D

because of their length, render the
assembly unserviceable. The crack shown
at B, although short, renders the assembly
unserviceable because it is within 0.375 in.
(9,525 mm) of the segment edge. The fine
surface cracks at X, Y and Z are permitted,
provided that the cracks do not extend to
the edge of the segment in the general
direction of P and R.
(d) Check for excessive waisting. Assessment of
condition must be based on service experience.
Waisting is a normal wear condition which has little
detrimental effect.
(e) Subject to serviceability as detailed in the previous
sub-paragraphs, place the assembly in the shrinkage
gauge. Subject one segment for shrinkage check.
Push the selected segment and those at 90 deg., 180
deg. and 270 deg. in the directions indicated by
arrows in Figure 503, using light hand pressure. MC JETS, S.A. DE C.V.
Check the tenon engagement and bore clearance of
the selected segment. The pin gauge provided must
not enter between the outer edge of the tenon and
the shrinkage gauge. The bore clearance must not be
less than F in . and if necessary may be restored by
dressing the inner edge of the segment. Repeat these
checks on all segments in turn.

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Rotor Shrinkage Gauge

Figure 503

B. Cylinder Assembly

(1) Examine the cylinder liners and pistons for damage and corrosion:
- Use a Norton R222J weight P100 cloth, or a smooth hone to remove light
damage, but do not to damage the surface finish and make sure that the
area of repair is clean. MC JETS, S.A. DE C.V.
(2) Examine the heat insulators for signs of surface damage or too much distortion.

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(3) Examine the springs for damage, distortion and corrosion. Do a

load deflection test. Reject a spring that is not to limits (Ref.
Fits and Clearances).

(4) Examine all circlips for distortion, corrosion and sufficient

strength to function. Reject an unserviceable circlip.

(5) Examine the retraction pins for distortion, corrosion and minimum
pin diameter 0.2005 in. (5,092 mm) (Ref. Fits and Clearances).

(6) Examine all remaining components for damage and corrosion.

C. Cylinder Block and Torque Tube

(1) Examine the cylinder block for damage and corrosion. Surface
damage to the cylinder block can be repaired (Ref. Repair No. 4).

(2) Examine all threads for good condition. Bleed screws can be
repaired (Ref. Repair No. 7).

(3) Examine the torque tube for damage and wear on the tenons. Minimum
tenon width is 0.560 in. (14,22 mm) (Ref. Fits and Clearances).

(4) Use a smooth-cut file to blend out the sharp edges of torque tube
tenons that are worn but in limits. Make sure to keep the relation
of angles between tenon faces and do not decrease the overall
width.

MC JETS, S.A. DE C.V.


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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

REPAIR

General

1. Special Tools, Equipment and Materials

A. Special Tools

NOTE: Alternatives can be used.

Tool List Description Remarks

Item No.

1 Tenon wear gauge Repair No. 1 and No. 3

4 Clamping plates Repair No. 2

17 Riveting set Repair No. 1 and No. 2

B. Equipment

NOTE: Alternatives can be used.

Item No. Item Remarks

1 Surface plate Repair No. 1 and No. 2

2 90 degree angle drill, 0.438 in. Repair No. 1 and No. 2

(11,1 mm) diameter

3 Drill, 0.0625 in. (1,6 mm) Repair No. 1 and No. 2

diameter

4 Parallel punch, not more than Repair No. 1 and No. 2

0.25 in. (6,35 mm) diameter

5 Press, 0 to 1.5 ton (1524 kg) Repair No. 1 and No. 2

6 Air circulating oven Repair No. 2

MC JETS, S.A. DE C.V.

General

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C. Materials
NOTE: Additional material information is listed at the applicable repairs.

NOTE: Equivalent alternatives can be used.

Material Specification Supplier/Remarks

1 Aluminium oxide grit, Repair No. 2

180 to 220 mesh
2 Primer IP-2066 Repair No. 3 and 5

3 Loctite 601 Repair No. 5

2. List of Material, Suppliers and Addresses

Item No. Supplier and Address Vendor Code

1 Local supply -
2 Indestructible Paints Ltd K3504
19-25 Pentos Drive
Sparkhill
Brimingham
B11 3TA
United Kingdom
3 Loctite Corp -
705 North Mountain Road
Newington
Connecticut 06111
USA
3 Henkel Limited U0406
Technologies House Wood Lane End
Hemel Hempstead
HP 2 4RQ
Herts
United Kingdom

MC JETS, S.A. DE C.V.

General
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3. List of Repairs

A. Repairs in this manual are:

Repair No. Title

1 Repair of Thrust and Pressure Plate Assemblies

2 Reclaim of Fully Worn Double Stator Assemblies

3 Reclaim of Cracked Stator Plates – RP678

4 Repair of Damage to the Cylinder Block Assembly

5 Repair of Oversize Pad Rivet holes in Pressure Plate – RP1197

6 Repair of Worn or Damaged Torque Tube Tenons – RP1040

7 Repair to the Bleed Screw Hole of the Cylinder Block – RP1231

8 Repair of Protective Paint Finish on the Cylinder Block

9 Replace the Insulator on a Piston (P/N AH088411)

MC JETS, S.A. DE C.V.

General
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE,
BRAKE, PART NO. AHA1897

REPAIR

Repair No. 1 - Repair of Thrust and Pressure Plate Assemblies

1. New Parts, Equipment and Materials

A. New parts

New Part No. Description Quantity

AHO83326-7 Packing piece up to 8

(replace as
required)

AHO83829-6 Pad assembly 8

AHO80972-1 Rivet (thrust plate) 8

or or
AHO80972-3 Rivet (pressure plate)

AHO82396 Rivet Plate (thrust plate) 8

NOTE: Rivet plates are not required for the pressure plate.

B. Equipment

Equipment Description Remarks

Machine tool, To machine

pilot drill 0.0625 in. (1,6 mm) diameter holes through
and pad retaining
90 degree 0.4375 in. (11,1 mm) diameter rivets
angled drill

Parallel punch 0.25 in. (6,35 mm) diameter To remove

rivets

Tenon wear Ref. Special Tools, Fixtures To check the

gauge and Equipment, Tool item No.1 width of tenon
slots
MC JETS, S.A. DE C.V.
File Smooth cut To remove sharp
edges

Feeler gauges - To check the

and surface twist of plates
table

Repair No. 1

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Equipment Description Remarks

Grit blasting Pressure pot or venturi type To remove light

machine corrosion

Riveting tool Ref. Special Tools, Fixtures To attach pads

set and Equipment, Tool item on to a thrust
No. 17 or pressure
plate

Press - To apply a load

of up to 1½ ton
(1524 Kg)

C. Materials

NOTE: Equivalent alternatives can be used.

Material Specification Supplier

Fused Alumina Mesh size: 180/220 Abrasive Developments

(Aluminium Limited
Hardness: 1700-2300 K100
oxide) grit Norman House
blast Henley-in-Arden
SOLIHULL
West Midlands B95 5AH
(K2769)

2. General

A. Worn Thrust (70) and Pressure (170) Plates

(1) Do this procedure to repair a thrust or pressure plate found to be

worn (Ref. Check).

(2) Refer to the Illustrated Parts List, Figure 1 to identify the item
numbers given in parentheses (brackets).

3. Repair Procedure
MC JETS, S.A. DE C.V.
A. Removal of the Pad Assemblies (100 or 190)

CAUTION: DO NOT DAMAGE THE RIVET HOLES OF THE THRUST OR PRESSURE PLATE
WHEN MACHINE DRILLING.

(1) From the pad side of the thrust (70) or pressure (170) plate, use
the pilot drill to centrally machine through the head of each pad
retaining rivet (80 or 180).

Repair No. 1

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(2) Use the 90 degree drill to gradually machine through the head of
each pad retaining rivet until only a thin wall section remains.

(3) Use the parallel punch to remove each pad retaining rivet.

(4) Lift off each pad assembly (100 or 190).

B. Examination

(1) Examine each packing piece (105 or 195). Reject a packing piece
that is damaged.

(2) Examine each rivet hole of the pressure plate (170) for wear.
Reject a plate with a rivet hole of more than 0.268 in. (6,8 mm)
diameter.

NOTE: Rivet holes of the thrust plate (70) are not working holes
since the thrust plate (70) is assembled with rivet plates.

(3) For a pressure plate (170) use a tenon wear gauge to do a check of
each tenon slot. Reject a pressure plate with a tenon slot of more
than 0.687 in. (17,45 mm) in width.

CAUTION: DO NOT FILE ABUTMENT FACES.

(4) For a pressure plate (170) make sure that there are no sharp edges
on the side faces of the tenon slots. Remove sharp edges with a
smooth file.

(5) Use the feeler gauges and surface table to check the twist of the
thrust (70) or pressure (170) plate around the outside edge of the
plate. Unless it can be corrected by cold planishing, reject a
plate with a gap of twist that is more than 0.030 in. (0,76 mm).

C. Corrosion

CAUTIONS: 1. MAKE SURE THAT THE BLAST MATERIAL IS NOT CONTAMINATED

WITH PARTICLES THAT CAN CAUSE ELECTROLYTIC ACTION.

2. MAKE SURE THAT GRIT BLAST EQUIPMENT AND PROCESS IS TO

MANUFACTURER’S/SUPPLIER’S RECOMMENDATIONS.

(1) Examine the thrust (70) or pressure (170) plate for corrosion. If MC JETS, S.A. DE C.V.
the depth of pitting is not more than 0.010 in. (0.254 mm) the
effected area and nickel plate can be grit blasted.

(a) In the blast machine, hold the jet head at a distance of 4 to

6 in. (100 to 150 mm) away from the surface being blasted and
at an angle of about 25 degrees.

Repair No. 1

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(b) Grit blast at a pressure of:

- 30 to 40 psi (2 to 3 bar) with a pressure pot machine
or
- 60 to 80 psi (4 to 5 bar) with a venturi type machine.

(c) Use a jet of filtered air to remove loose and unwanted

material from the component.

(d) Clean the component (Ref. Cleaning) and re-plate it with

nickel (Ref. DEF STAN 03-10) to a depth of 0.0003 to
0.0005 in. (0.008 to 0.013 mm).

D. Installation of New Pad Assemblies (100 or 190)

(1) Use the riveting tool (Ref. Figure R1-601) to attach each pad
assembly to the thrust (70) or pressure (170) plate.

(a) Assemble the peening punch of the riveting tool with its
pressure plate, rubber pad and washer (Ref. Figure R1-601).

MC JETS, S.A. DE C.V.

Riveting Tool Set

Figure 601

Repair No. 1
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(b) Install the peening punch assembly in the tool holder

(Ref. Figure R1-601).

(c) Install the peening peg to the base plate of the riveting tool
(Ref. Figure R1-601).

(d) Replace rejected packing pieces (105 or 195) as required.

(e) Position a new pad (100 or 190) and packing piece on the
thrust (110) or pressure (200) plate. Make sure to engage the
projections on the back plate of the pad assembly with the
holes in the thrust or pressure plate.

(f) Put a rivet (80 or 180) to engage its pre-formed head in the
center of the pad assembly (100 or 190).

(g) Put the thrust or pressure plate, packing piece, pad and rivet
assembly on the base plate of the riveting tool to engage the
pre-formed head of the rivet (80 or 180) on the peening peg.

(h) Position a new rivet plate (90) on to the tail end of the
rivet (for a thrust plate assembly (70) only, part not
required for a pressure plate assembly (170)).

(i) Use the riveting tool to slowly apply a press load of up to

1½ ton (1524 Kg) to fully form the head of the rivet.

(j) Make smooth the rivet so that it is flush on the non-pad side
of the thrust or pressure plate.

(2) Make sure that each rivet is satisfactory and that each pad
assembly is tightly held.

(3) Examine for cracks at each rivet and each pad assembly around the
near area of the rivet. Cracks up to 0.0313 in. (0,8 mm) deep are
permitted around the near area of the rivet, but there must be no
more than two per rivet and angle spacing must be no less than
90 degrees apart.

(4) Position the Thrust or Pressure Plate assembly on a surface table

with the pad assemblies face down and use the feeler gauges to
check the twist of the thrust (70) or pressure (170) plate MC JETS, S.A. DE C.V.
assembly. The gap of twist must not be more than 0.030 in.
(0,76 mm).

Repair No. 1

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~DUNLDP LIM
COMPONENT MAINTENANC~ ,
PART NO.AHA 1897

Repair No. teclaim of Fully Worn Double Stator Assemblies

1. An unserviceable or fully worn double stator assembly may be reclaimed, for use
in a new heat pack, as detailed in the following instructions.

CAUTION: EXERCISE CARE WHEN DRILLING THE PAD RETAINING RIVETS TO

AVOID DAMAGE TO THE PLATE RIVET HOLES

A. Drill centrally through the head of each pad retaining rivet using a pilot
drill of 0.0625 in. (1,6 mm) diameter. Using a 90 deg. angle drill of 0.4375
in. (11,1 mm) diameter progressively drill the rivet head until only a th in
wall section remains. Using a parallel punch not exceeding 0.25 in .
(6,35 mm) diameter, remove each rivet and lift off the pads. If the packing
pieces f itted between the pads and plate are damaged during rivet
removal, they must be renewed with the pads.

B. Examine the stator plate for cracks, if doubt exists regarding the presence
of a crack, serviceability should be confirmed by magnetic crack detection
process. Cracked plates may be reclaimed if within the limits of Repair No.
3.

C. Check the pad rivet holes in the plate for shrinkage and distortion .
Distortion must not exceed 0.641 in. (16,28 mm) . Where shrinkage has
occurred the hole may be reamed to 0.630/0.636 in . (16,00/16,15 mm)
diameter.

CAUTION: DO NOT FILE OR DRESS THE ABUTMENT FACES.

D. Check for burrs on the side faces of the tenon slots. Remove any burrs with
a smooth file.

E. Place the stator plate on a surface plate and check that a 0.015 in .
(0,38 mm) feeler gauge cannot be inserted under any section of the plate, if
the amount of dishing exceeds this limit the plate should be flattened as
detailed in the following paragraphs.

F. Using special tool (Tool Item No.4) clamp the dished plate and soak at a
temperature of 700 deg.C (1292 deg .F)for a period of 5 hours . Allow to
cool, remove from special tool (Tool Item No.4) and repeat sub-para.E.

1. By substituting longer clamping bolts in special tool(Tool

Item No.4) several plates may be flattened at once .

2. If facilities for heat treatment are not available, cold

planishing may be used to bring dished plates within the
limits of sub-para.E.

G. Using inert aluminium oxide grit of 180 to 220 mesh, le plate by grit
blasting both sides of the stator plate. On completio aning, check
that the thickness of the stator plate is not lessthan 0.125 in. (3,18 mm).

REPAIR

Repair NO.2
Page 601
DAI/3133/50 32 - 43 ~ 26 June10/91
PRINTED IN ENGLAND
MC JETS, S.A. DE C.V.
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PART NO.AHA1897

H. Carry out a further examination for cracks as detailed in sub-para. 8.

I. Using special tool (Tool Item No. 17) secure the pads to the plate as follows.

(1) Fit the pressure plate and rubber pad to the peening punch and
secure in the tool holder.

(2) Fit the peening peg to the base plate.

(3) Fit the packing piece and position new pads on both sides of the
stator piate, ensuring that the projections on the back of the pads
engage the holes in the stator plate, insert a rivet.

(4) Position the plate assembly so that the pre-formed head of the rivet
~~~~~~~)~~~~n;f:;~rt~~~~~;~o:~:r.apply a pressload up to 1t ton
J. Check that the riveting is satisfactory and that each pad is firmly held.
Examine each rivet and pad friction face for cracks, particularly in the
immediate vicinity of the rivet. Small cracks up to 0.0313 in. (0,8 mm) deep
are permissible around the periphery of the rivet only, providing there are
not more than two per rivet and the spacing is not lessthan 90 deg.

K. After riveting place the stator assembly flat on the surface plate and check
for distortion which should not be in excess of 0.020 in. (0,51 mm).

MC JETS, S.A. DE C.V.

REPAIR

Repair No.2
Page 602
CO: 9612

DA1/3133/50 32 - 43 - 26 June10/91
PRINTED IN ENGLAND
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HYDRAULIC PLATE BRAKE, PART NO. AHA1897
REPAIR

Repair No. 3 – Reclaim of Cracked Stator Plates RP678

1. Stator plates rejected for cracks, distortion or shrinkage during Repair No. 2 may be reclaimed
as detailed in the following instructions:

A. Ensure the stator plate is clean and free from greases.

B. Check the stator plate bore diameter and the dimensions between the bases of opposite
tenon slots. Those found to be below the minimum return to service dimensions must be
machined to the original dimensions, refer to Figure 601. Ensure the operation has not
reduced the plate width below the reference dimensions given in Figure 601. Restore the
corner radii of the slots.

C. Check the outer diameter of the stator plate, when found to be greater than the maximum
return to service dimensions the diameter must be reduced to the original.
Refer to Figure 601.

MC JETS, S.A. DE C.V.

Stator Plate Machining Details

Figure 601

Repair No. 3
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D. Measure the tenon slot width. When found to be below the nominal width they should be
restored to the original dimensions, refer to Fits and Clearances, ensuring that the corner
radii are maintained.

E. Machine or dress out any cracks at the root of the tenon slots or relief holes to the
dimensions given in Figure 601. If the cracks are not wholly recovered after this repair has
been carried out, the plate must be rejected.

F. Remove all sharp edges from the machined or dressed areas.

G. On satisfactory completion of the repair, vibro-etch RP678/1 or RP678/2 for a first or

second repair, as applicable, adjacent to the plate part number.

H. Restore the protective treatment:

(1) Clean the stator plate (Ref. Cleaning).

(2) Mix the primer IP-2066 in accordance with the paint manufacturer instructions.

(3) Apply a coat of primer IP-2066.

MC JETS, S.A. DE C.V.

Repair No. 3
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REPAIR

Repair No. 4 – Repair of Damage to the Cylinder Block Assembly

1. Materials

NOTE: Equivalent alternatives can be used.

Material Specification Supplier

Norton R222 J weight - Saint-Gobain Abrasives Limited

P100 cloth Doxey Road
Stafford
ST16 1EA
United Kingdom
(Vendor code KC1D9)

Smooth hone - Local supply

Chromate conversion MIL-DTL-5541

solution, for brush / swab (DEF STAN 03-18)
use

- Alodine 1200 Local supply

- Brush Alocrom 1200 ICI Paints

Wexham Road
Slough
Berkshire
SL2 5DS
United Kingdom
(Vendor code K2054)

Nylon brush or - Local supply

Cotton swab

Hydrocarbon cleaning fluid Class III blend of Local supply, or

hydrocarbons

- Lotoxane Reabrook Limited

(Class III) T/A Arrow Chemicals
Rawdon Road
Moira Swadlincote MC JETS, S.A. DE C.V.
Derbyshire DE12 6DA
United Kingdom
(Vendor code U0698)

Continued...

Repair No. 4
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Material Specification Supplier

- Multisol M56 Multisol Ltd

(Class III) Welsh House
83 Welsh Row
Nantwich
Cheshire
CW5 5ET
United Kingdom
(Vendor code KCVF8)

Cloth, lint-free - Local supply

Disposable paper tissues - Local supply

2. Repair Procedure

A. Removal of Damage

(1) Use a Norton R222 J weight P100 cloth or a smooth hone to remove surface
damage or corrosion. Make sure that there are no sharp edges and that the surface
of the repair has a smooth contour.

(2) If external damage or surface corrosion cannot be removed by polishing out, reject
the component.
B. Repair of the Surface Protection

WARNING: HYDROCARBON CLEANING FLUID IS HAZARDOUS MATERIAL. BEFORE

YOU USE IT, MAKE SURE THAT YOU KNOW THE SAFETY
PRECAUTIONS AND FIRST AID INSTRUCTIONS ON:
- THE LABELS ON THE CONTAINER IT WAS SUPPLIED IN
- ITS MATERIAL SAFETY DATA SHEET
- YOUR LOCAL SAFETY REGULATIONS.

(1) Fully clean the area of repair with hydrocarbon cleaning fluid (Ref. Cleaning).

(2) Dry the cleaned surface.

MC JETS, S.A. DE C.V.

Repair No. 4
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WARNING: CHROMATE CONVERSION SOLUTIONS, AND THEIR CHEMICAL

CONSTITUENTS, ARE HAZARDOUS. BEFORE YOU USE THEM, MAKE
SURE YOU KNOW THE SAFETY PRECAUTIONS AND FIRST AID
INSTRUCTIONS ON:
- THE LABELS ON THE CONTAINERS THEY WERE SUPPLIED IN
- THE MATERIAL SAFETY DATA SHEET(S)
- YOUR LOCAL SAFETY REGULATIONS.

(3) Use a nylon brush or cotton swab to apply the chromate conversion solution on the
bare metal to MIL-DTL-5541 or DEF STAN 03-18.

NOTE: The procedure which follows is an example of the steps that you must do.
But, obey the instructions given by the manufacturer of the chemical
conversion solution that you use.

(a) Obey the manufacturer’ s instructions and:

1 Prepare a chromate conversion solution to be applied with brush or swab.

NOTE: Prepare only sufficient chromate conversion solution for

immediate use.

CAUTION: KEEP THE CHROMATE CONVERSION SOLUTION OUT OF

CREVICES AND SEAMS.

2 Use a nylon brush or a cotton swab to apply the chromate conversion

solution on the bare metal to MIL-DTL-5541 or DEF STAN 03-18.

3 Use clean water, maximum temperature 50 deg. C (122 deg. F) to flush

all chromate conversion solution from the item. It is recommended that
the item be finally flushed with de-mineralized water.

4 Dry the item in clean air, maximum temperature 60 deg. C (140 deg. F).

5 Repair the paint finish (Ref. Repair No. 8).

MC JETS, S.A. DE C.V.

Repair No. 4
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HYDRAULIC PLATE BRAKE, PART NO. AHA1897

REPAIR

Repair No. 5 – Repair of Oversize Pad Rivet Holes in Pressure Plate – RP1197

1. Pressure plates that have worn or damaged retaining holes are to have a shouldered washer
fitted, as detailed in the following instructions:

A. Machine the hole under repair to the dimensions given in Figure 601, Location A.

Machining and Fitting Details

Figure 601

B. Restore the protective treatment:

(1) Clean the pressure plate (Ref. Cleaning).

(2) Mix the primer IP-2066 in accordance with the paint manufacturer instructions.

(3) Apply a coat of primer IP-2066.

(4) Allow the protective treatment to dry.

MC JETS, S.A. DE C.V.
C. After degreasing or solvent cleaning of the shouldered washer and relevant areas, allow
to dry.

Repair No. 5
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WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE
MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A
CONSUMABLE MATERIAL.

D. Coat the mating surfaces of the plate and shouldered washer sparingly with Loctite 601
and assemble ensuring the shouldered washer is flush with the pressure plate.
See Figure 601, Location B.

E. Allow the assembly to cure at a room temperature for at least 4 hours.

F. Brake pad assemblies are to be renewed to the instructions given in Repair No. 1
para 3.D.

G. After satisfactory completion of this repair, vibro-etch RP1197 adjacent to the part
numbers on the pressure plate.

H. Restore the protective treatment by application of a coat of primer IP-2066.

2. New Component

Part No. Description No. off

AH089621 Shouldered Washer As required

MC JETS, S.A. DE C.V.

Repair No. 5
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HYDRAULIC PLATE BRAKE, PART NO. AHA1897
REPAIR

Repair No. 6 – Repair of Worn or Damaged Torque Tube Tenons – RP1040

1. New Parts and Materials

A. New Parts

New Part No. Description Quantity

AH089465 Tenon Sleeve 8

SP76-408 Rivet 8
DSR669-6

B. Materials
NOTE: Alternatives can be used.

Material Specification Supplier

Primer IP-2066 Indestructible Paints Ltd

19-25 Pentos Drive
Sparkhill
Brimingham
B11 3TA
United Kingdom
Vendor Code K3504

2. References and General Instructions

A. References

(1) Disassembly.

(2) Cleaning.

B. General Instructions

(1) Item numbers in brackets (parenthesis) are those shown in

Figure 301 (Ref. Disassembly). MC JETS, S.A. DE C.V.
(2) Disassemble the torque tube assembly (460) (Ref. Disassembly).

(3) Clean the torque tube assembly (460) (Ref. Cleaning).

(4) Do this repair if one or more torque tube tenons are damaged or have a width of
less than 0.560 in. (14,22 mm).

Repair No. 6
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3. Repair Procedure

A. Machining and Paint Protection

(1) Machine all eight tenons of the torque tube assembly (Ref. Figure R6-601).

NOTE: Each torque tube tenon has a rivet hole after machining.

(2) Apply a layer of primer IP-2066 on the machined surfaces of the torque tube
assembly in accordance with the paint manufacturer instructions.

(3) Let the paint protection dry.

MC JETS, S.A. DE C.V.

Machined Dimensions of a Repaired Torque Tube

Figure R6-601

Repair No. 6
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B. Installation of the Tenon Sleeves

(1) Use a rivet on each tenon sleeve and attach a tenon sleeve to each torque tube
tenon (Ref. Figure R6-602).

Installation of a Tenon Sleeve on a Torque Tube

Figure R6-602

(2) Make each rivet smooth (flush) to the tenon sleeve surface.

C. Identification and Paint Protection of the Repair

(1) Use vibro-peen and put RP1040 (the repair number) on one tenon sleeve
(Ref. Figure R6-602).

(2) Apply a layer of primer IP-2066 on all areas where rivets were made smooth and
where vibro-peen was applied.

D. Assemble the torque tube assembly (460) (Ref. Assembly (Including Storage)).

MC JETS, S.A. DE C.V.

Repair No. 6
Page 603/604 Blank
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HYDRAULIC PLATE BRAKE, PART NO. AHA1897
REPAIR

Repair No. 7 – Repair to the Bleed Screw Hole of the Cylinder Block – RP1231

1. New Parts, Equipments and Materials

A. New Parts

Part Number Description Quantity

AH089931 Sleeve 1

DAS2119-6 O-ring seal 1

B. Equipments

(1) Machine tool and thread tap to machine a hole and tap a 9/16-18UNFJ-3B thread
(Ref. Figure R7-601).

(2) A set of 1/8 in. (3 mm) high character, metal stamps to put identity markings on the
brake unit.

C. Materials

NOTE: Equivalent alternatives can be used.

Material Specification Supplier

Araldite DBF - Local supply

Hardener HY 951 - Local supply

Parker O-Lube - Parker Hannifin Seal Group

O-Ring Division
2360 Palumbo Drive
PO Box 11751
LEXINGTON
KY 40512
USA

2. References MC JETS, S.A. DE C.V.

A. Disassembly.

B. Repair No. 4.

C. Repair No. 8.

D. Assembly (Including Storage).

Repair No. 7
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3. Repair Procedure

A. Disassembly

(1) Disassemble the hydraulic plate brake to remove the cylinder block
(P/N AH089791) (Ref. Disassembly).

B. Machine the Damaged Bleed Screw Hole

(1) Machine and tap the damaged bleed screw hole of the cylinder block to the
dimensions specified for the new hole (Ref. Figure R7-601).

(2) Inspect the new machined and tapped hole to make sure that it is satisfactory and
that all damage has been removed.

C. Surface Protection

(1) Repair the surface protection (Ref. Repair No. 4).

D. Assembly

WARNING: YOU MUST OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE
MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A
CONSUMABLE MATERIAL.

(1) Apply a thin layer of Parker O-Lube on the O-ring seal (P/N DAS2119-6).

(2) Install the O-ring seal (P/N DAS2119-6) on the sleeve (P/N AH089931).

(3) Remove all Parker O-Lube from the threads of the sleeve (P/N AH089931).

(4) Mix the Araldite DBF with the Hardener HY 951 in accordance with the
manufacturer’s instructions.

(5) Apply a layer of mixed Araldite DBF to the internal threads of the new machined
and tapped hole.

(6) Install the sleeve (P/N AH089931) with O-ring (P/N DAS2119-6) in the new
machined and tapped hole (Ref. Figure R7-602).

(7) Torque the repair sleeve to 10 lbf ft (13,56 Nm).

(8) Remove all unwanted Araldite. MC JETS, S.A. DE C.V.

(9) Allow to cure the Araldite DBF in accordance with the manufacturer’s instructions.

Repair No. 7
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E. Record that the Repair has been done

(1) Use 1/8 in. (3 mm) character stamps and put (adjacent to the brake unit part
number) the repair number, RP1231.

(2) Protect bare metal surfaces with:

- Repair the surface protection (Ref. Repair No. 4)
- Touch-up paint finish (Ref. Repair No. 8).

F. Assemble the hydraulic plate brake (Ref. Assembly (Including Storage)).

MC JETS, S.A. DE C.V.

Repair No. 7
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MC JETS, S.A. DE C.V.

Dimensions of the Machined and Tapped Hole

Figure 601

Repair No. 7
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Sleeve and O-ring Seal Installation

Fig. 602

MC JETS, S.A. DE C.V.

Repair No. 7
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HYDRAULIC PLATE BRAKE, PART NO. AHA1897
REPAIR
Repair No. 8 – Repair of Protective Paint Finish on the Cylinder Block

1. Equipment and Materials

NOTE: Equivalent alternatives can be used.

A. Equipment

(1) An air circulating oven which can give a controlled temperature of 90 deg. C
(194 deg. F).

(2) Paint spray equipment and room.

(3) BS1733 B3 flow cup.

(4) BS3900 B3 flow cup.

B. Materials

Material Specification Supplier (Vendor code)

Epoxy primer PR143 PPG Industries (UK) Ltd

Darlington Road
SHILDON
DL4 2QP
England

Activator No. 143 As above

Thinner T17 (TH84) As above

Epoxy finish silver EC75 As above

Activator No. 65 As above

Polyurethane finish FE93 As above

(Color: Silver)

Activator No. 93 As above

Thinner T115 As above

2-pack low VOC IP6-C9031 Indestructible Paint Limited MC JETS, S.A. DE C.V.
polyurethane topcoat 19-25 Pentos Drive
(Color: Silver) Sparkhill
Birmingham
B11 3TA
England
(Vendor Code K3504)

Continued . . .
Repair No. 8
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Material Specification Supplier (Vendor code)

2-pack low VOC IP6-CAT As above

polyurethane catalyst

Reducer/Thinner IP-MEG-REDUCER As above

2-Butanone (Methyl- - Local supply

Ethyl-Ketone (MEK))

Emery cloth 360 or finer grade Local supply

Cloth, lint-free - Local Supply

2. References and General Instructions

A. References

(1) Disassembly.

(2) Cleaning.

(3) Repair No. 4.

B. General Instructions

(1) Do all paint procedures in an area with a good flow of air.

(2) Prepare materials and complete the paint protection in an area that has a
temperature of between 15,5 deg. C and 21,0 deg. C (60 deg. F and 70 deg. F).
Humidity must be less than 75%.

(3) Air drying must be carried out in a clean, dust free area, with the temperature
maintained above 15,5 deg. C (60 deg. F) and relative humidity below 75%.

(4) Force drying or stoving must be carried out in air-circulated oven. The cylinder
block should be allowed to reach oven temperature slowly to prevent blistering and
maintained at a specific temperature for the time required.

(5) Make sure that the cylinder block is clean.

(6) Make sure that the cylinder block is serviceable. Do repairs as necessary. MC JETS, S.A. DE C.V.
(7) Make sure that the bolt holes and other areas, where paint is not necessary, have
protection.

(8) Always let a force dried cylinder block to a temperature of 15,5 deg. C to
21,0 deg. C (60 deg. F to 70 deg. F) before you apply more paint.

(9) It is recommended not to use the repaired cylinder block for the first week after a
paint protection repair (maximum solvent resistance occurs after seven days).
Repair No. 8
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3. To Prepare Paint Materials

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE MANUFACTURER

AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A CONSUMABLE
MATERIAL.
A. Mixing Instructions for Epoxy Primer PR143

(1) Fully mix the epoxy primer PR143. Make sure that all pigment at the bottom of the
container is mixed.

(2) Fully mix together one part by volume, of activator No. 143 to two parts by volume,
of the stirred epoxy primer PR143.

(3) Make sure that the viscosity is 26 to 30 seconds using BS3900 B3 flow cup. Use
thinner T17 (TH84) to adjust the viscosity if necessary.

NOTE: Wait for 15 minutes, before you use the mixed epoxy primer PR143.

NOTE: The pot life of the mixed epoxy primer PR143 is eight hours.

(4) Stir the mixture before use.

(5) Put the caps back on the container after use.

B. Mixing Instructions for Epoxy Finish EC75 Silver

(1) Fully mix the epoxy finish EC75 silver. Make sure that all pigment at the bottom of
the container is mixed.

(2) Fully mix together one part by volume, of activator No. 65 to one part by volume, of
the stirred epoxy finish EC75 silver.

(3) Make sure that the viscosity is 30 to 35 seconds using BS3900 B3 flow cup. Use
thinner T17 (TH84) to adjust the viscosity if necessary.

NOTE: Wait for 15 minutes, before you use the mixed epoxy finish EC75 silver.

NOTE: The pot life of the mixed epoxy finish EC75 silver is eight hours.

(4) Stir the mixture before use.

(5) Put the caps back on the container after use.

C. Mixing Instructions for Polyurethane Finish FE93 (Color: Silver) MC JETS, S.A. DE C.V.
NOTE: If polyurethane finish FE93 is not available, use 2-pack low VOC polyurethane
topcoat IP6-C9031 (Ref. Para 3.D.).

(1) Fully mix the polyurethane finish FE93. Make sure that all pigment at the bottom of
the container is mixed.

Repair No. 8
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(2) Fully mix together one part by volume, of activator No. 93 to two parts by volume,
of the stirred polyurethane finish FE93.

(3) Make sure that the viscosity is 26 to 32 seconds using BS3900 B3 flow cup. Use
thinner T115 to adjust the viscosity as necessary.

NOTE: Wait for 15 minutes, before you use the mixed polyurethane finish FE93.

NOTE: The pot life of the mixed polyurethane finish FE93 is eight hours at
21 deg. C (70 deg. F) and four hours at 35 deg. C (95 deg. F).

NOTE: The storage life of polyurethane finish FE93 is 24 months when stored
between 5 deg. C and 35 deg. C (41 deg. F and 95 deg. F).

NOTE: Activator No. 93 is moisture sensitive. Use the activator as quickly as

possible after the container has been opened. Discard the activator if it
shows signs of separation or gelling.

(4) Stir the mixture before use.

(5) Put the caps back on the container after use.

D. Mixing Instructions for 2-Pack Low VOC Polyurethane Topcoat IP6-C9031

(Color: Silver)

(1) Fully mix the 2-pack low VOC polyurethane topcoat IP6-C9031. Make sure that all
pigment at the bottom of container is mixed.

(2) Mix only the amount that can be used in one hour. This paint will thicken on
standing.

(3) Slowly add the 2-pack low VOC polyurethane catalyst IP6-CAT to the 2-pack low
VOC polyurethane topcoat IP6-C9031 base component using the specified mix
ratio. Indestructible Paints specify the mix ratios as a mix by volume.

(4) Add IP-MEG-REDUCER reducer/thinner 10% by volume to adjust viscosity. This

should be 60 to 70 seconds using BS1733 B3 Flow Cup at 20 deg. C (68 deg. F).

NOTE: Wait for 15 minutes minimum before using the mixed 2-pack low VOC
polyurethane topcoat IP6-C9031.

NOTE: The pot life of the 2-pack low VOC polyurethane topcoat IP6-C9031 is
one hour. The storage life of 2-pack low VOC polyurethane topcoat
IP6-C9031 is 12 months when stored between 5 deg. C and 35 deg. C MC JETS, S.A. DE C.V.
(41 deg. F and 95 deg. F).

(5) Put the caps back on the container after use.

Repair No. 8
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
4. To Prepare the Cylinder block

A. For a General Repair

(1) Fully disassemble the cylinder block assembly (Ref. Disassembly).
(2) Clean the cylinder block (Ref. Cleaning).

(3) Repair the surface finish of the cylinder block and apply chromate conversion
solution (Ref. Repair No. 4).

(4) Mask off the areas where paint finish is not required.

B. For Touch-up Repair (Less than 5% of Total Surface Area)

(1) Clean the cylinder block (Ref. Cleaning).
(2) Make sure the surface of the paint damaged area is satisfactory for paint repair
(Ref. Repair No. 4).

(3) Use emery cloth (360 grade or finer grade) to remove damage or corrosion. Make
sure that there are no sharp edges and that the surface of the repair has a smooth
contour.

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE

MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A
CONSUMABLE MATERIAL.

(4) Clean the damaged area with 2-Butanone (Methyl-Ethyl-Ketone (MEK)) using a
clean, lint free cloth.

(5) Repair the surface finish of the cylinder block and apply chromate conversion
solution (Ref. Repair No. 4).

(6) Mask off the areas where paint finish is not required.

5. To Apply Paint Protection

NOTES: 1. Method II is an alternative for Method I.

2. If polyurethane finish FE93 (Ref. Para 5.A. and 5.C.) is not available, use
2-Pack low VOC Polyurethane Topcoat IP6-C9031 (Ref. Para 5.B. and 5.D.).

A. General Repair – Method I (Polyurethane Finish FE93 (Color: Silver))

MC JETS, S.A. DE C.V.
WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE
MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A
CONSUMABLE MATERIAL.
(1) Apply one double track spray coat of epoxy primer PR143. Apply the paint to give a
minimum dry thickness of 0.0005 in. (13 μm).

(2) Air dry for four hours or force dry at 90 deg. C (194 deg. F) for one hour.

Repair No. 8
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(3) Apply one double track spray coat of epoxy finish EC75 silver. Apply the paint to
give a minimum dry thickness of 0.0005 in. (13 μm).
(4) Air dry for four hours or force dry at 90 deg. C (194 deg. F) for one hour.

(5) Apply one double track spray coat of epoxy primer PR143. Apply the paint to give a
minimum dry thickness of 0.0005 in. (13 μm).
(6) Air dry for four hours or force dry at 90 deg. C (194 deg. F) for one hour.

(7) Apply one double track spray coat of polyurethane finish FE93.

(8) Allow polyurethane finish FE93 to air dry for one hour.

(9) Apply second or more double track coat of polyurethane finish FE93.
Do this until there is sufficient coats (minimum of two) to give a minimum dry
thickness of 0.0015 in. (38 μm).
(10) Air dry the last layer of polyurethane finish FE93 for six hours (or more) or flash-off
for 15 minutes at an ambient temperature and force dry at 90 deg. C (194 deg. F)
for one hour.
(11) Make sure that the paint protection:
- Has a satisfactory finish (some orange peel effect is permitted, but no
runs, sags, pinholes, streaks, blisters, lifting or other damage)
- Has a minimum total thickness of 0.003 in. (76 μm).

The dry thickness of the system must be as follows:

Epoxy Primer PR143 (1 coat) 0.0005 in. (13 μm) min

Epoxy Finish EC 75 Silver (1 coat) 0.0005 in. (13 μm) min
Epoxy Primer PR143 (1 coat) 0.0005 in. (13 μm) min
Polyurethane Finish FE 93 0.0015 in. (38 μm) min
(2 coats min)
Total film thickness 0.003 to 0.0045 in. (76 to 114 μm)
(12) Remove the masking protection.

B. General Repair – Method II (2-Pack Low VOC Polyurethane Topcoat IP6-C9031

(Color: Silver))

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE

MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A
CONSUMABLE MATERIAL. MC JETS, S.A. DE C.V.

(1) Apply one double track spray coat of epoxy primer PR143. Apply the paint to give a
minimum dry thickness of 0.0005 in. (13 μm).

(2) Air dry for four hours or force dry at 90 deg. C (194 deg. F) for one hour.
(3) Apply one double track spray coat of epoxy finish EC75 silver. Apply the paint to
give a minimum dry thickness of 0.0005 in. (13 μm).

Repair No. 8
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(4) Air dry for four hours or force dry at 90 deg. C (194 deg. F) for one hour.

(5) Apply one double track spray coat of epoxy primer PR143. Apply the paint to give a
minimum dry thickness of 0.0005 in. (13 μm).
(6) Air dry for four hours or force dry at 90 deg. C (194 deg. F) for one hour.

(7) Apply one double track spray coat of 2-pack low VOC polyurethane topcoat
IP6-C9031.

(8) Allow 2-pack low VOC polyurethane topcoat IP6-C9031 to air dry for
15 minutes.
(9) Apply second or more double track coat of 2-pack low VOC polyurethane topcoat
IP6-C9031. Do this until there is sufficient coats (minimum of two) to give a
minimum dry thickness of 0.0015 in. (38 μm).

(10) Air dry the last layer of 2-pack low VOC polyurethane topcoat IP6-C9031 for
24 hours (or more) or flash off for 30 minutes minimum at ambient temperature and
force dry at 90 deg. C (194 deg. F) for 90 minutes.
(11) Allow 2-pack low VOC polyurethane topcoat IP6-C9031 to cool for 30 minutes in
ambient temperature before touching.
(12) Make sure that the paint protection:
- Has a satisfactory finish (some orange peel effect is permitted, but no
runs, sags, pinholes, streaks, blisters, lifting or other damage)
- Has a minimum total thickness of 0.003 in. (76 μm).
The dry thickness of the system must be as follows:

Epoxy Primer PR143 (1 coat) 0.0005 in. (13 μm) min

Epoxy Finish EC 75 Silver (1 coat) 0.0005 in. (13 μm) min
Epoxy Primer PR143 (1 coat) 0.0005 in. (13 μm) min
2-pack low VOC polyurethane topcoat 0.0015 in. (38 μm) min
IP6-C9031 (2 coats min)
Total film thickness 0.003 to 0.0045 in. (76 to 114 μm)
(13) Remove the masking protection.

C. Touch-up Repair – Method I (Polyurethane Finish FE93 (Color: Silver))

WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE
MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A MC JETS, S.A. DE C.V.
CONSUMABLE MATERIAL.

(1) Apply a thin layer of epoxy primer PR143 to the area of repair. Make sure that the
edges of the epoxy primer PR143 overlap the edges of the serviceable paint.

(2) Allow to air dry for four hours.

(3) Apply one layer of epoxy finish EC75 silver.

Repair No. 8
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(4) Allow to air dry for four hours.

(5) Apply a thin layer of epoxy primer PR143.

(6) Allow to air dry for four hours.

(7) Apply one layer of polyurethane finish FE93. Make sure that the contours of the
repair and the serviceable paint are smooth.
NOTE: If it is necessary to apply two or more layers of polyurethane finish FE93,
then let the paint dry in air for 15 minutes between applications.

(8) Let the polyurethane finish FE93 paint to air dry for more than six hours.

(9) Remove the masking protection.

D. Touch-up Repair – Method II (2-Pack Low VOC Polyurethane Topcoat IP6-C9031

(Color: Silver))
WARNING: OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE
MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE A
CONSUMABLE MATERIAL.

(1) Apply a thin layer of epoxy primer PR143 to the area of repair. Make sure that the
edges of the epoxy primer PR143 overlap the edges of the serviceable paint.

(2) Allow to air dry for four hours.

(3) Apply one layer of epoxy finish EC75 silver.

(4) Allow to air dry for four hours.

(5) Apply a thin layer of epoxy primer PR143.

(6) Allow to air dry for four hours.

(7) Apply one layer of 2-pack low VOC polyurethane topcoat IP6-C9031. Make sure
that the contours of the repair and the serviceable paint are smooth.
NOTE: If it is necessary to apply two or more layers of 2-pack low VOC
polyurethane topcoat IP6-C9031 then let the paint dry in air for 15 minutes
between applications.
(8) Let the 2-pack low VOC polyurethane topcoat IP6-C9031 to air dry for MC JETS, S.A. DE C.V.
24 hours.
(9) Remove the masking protection.

Repair No. 8
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
REPAIR

Repair No. 9 – Replace the Insulator on a Piston (P/N AH088411)

1. Equipment and Materials

NOTE: Equivalent items can be used.

A. Equipment

(1) An air circulating oven which can give a controlled temperature of 150 deg. C
(302 deg. F).

(2) Applicable clamp.

(3) Machining Equipment.

B. Materials

Material Specification Supplier

2-Butanone (Methyl- - Federal Specifications

Ethyl-Ketone (MEK)) Promulgated by General
Services Administration
Washington DC
NATL Institute STDS & TECH
100 Bureau DR
MD 20899
USA
(Vendor Code 81348)

Optional

Ethyl Acetate - Local supply

Adhesive Bostik 1777 The Pekay Group (PTY) Ltd

P O BOX 43116
Industria 2042
South Africa
Threebond TB2210 Three Bond Europe SAS
(UK Branch)
12 Erica Road MC JETS, S.A. DE C.V.
Stacy Bushes
Milton Keynes
MK 126HS
United Kingdom
Continued…

Repair No. 9
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HYDRAULIC PLATE BRAKE, PART NO. AHA1897
B. Materials (Continued)

Material Specification Supplier

Norton R222 J Weight - Saint-Gobain Abrasives Limited

P100 cloth Doxey Road
Stafford
ST16 1EA
United Kingdom
(Vendor Code KC1D9)

Lint free cloth - Local supply

Loctite 7063 - Local supply

or
Loctite 7070

2. New Parts

Part Number Description Item per Assy

AH083149 Insulator (non asbestos) 1

DMS 661 Stainless steel
sintered with mica

3. General Instructions

A. There are two methods of bonding insulator to piston:

- Method 1 – Use Threebond TB2210 to bond insulator to piston (Ref. Para 5)
- Method 2 – Use Bostik 1777 to bond insulator to piston (Ref. Para 6.).

B. MABS recommend that method 1 is used.

C. Method 2 requires more care and correct tooling to achieve consistent results.

4. Procedure

A. Preparation

CAUTION: BE CAREFUL THAT YOU DO NOT DAMAGE THE PISTON WHEN YOU
REMOVE THE WORN HEAT INSULATOR. MC JETS, S.A. DE C.V.

(1) Machine the heat insulator (insulator) out of the piston.

(2) Rub the area of the piston which is to be bonded with Norton R222 J Weight P100
cloth.

Repair No. 9
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
5. Method 1 - Use Threebond TB2210 to bond insulator to piston

WARNING: YOU MUST OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE
MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE THE
CONSUMABLE MATERIALS.

A. Bonding Procedure

(1) Clean the mating surfaces of the piston and insulator with loctite 7063 or loctite 7070.

(2) Apply a layer of adhesive Threebond TB2210 to the mating faces of piston and
insulator including the edges of the insulator pad.

(3) Put the insulator pad into the end of the piston.

NOTE: It is recommended that a clamping fixture with a clamping pressure of 3,4 to

13,8 bar (50 to 200 psi) is used to hold the insulator and piston.

(4) The length of the piston assembly must not be more than 1.487 in. (37,77 mm)
(Ref. Figure R9-601).

WARNING: PUT ON HEAT RESISTANT GLOVES WHEN YOU PUT PISTON ASSEMBLY
IN A HOT AIR CIRCULATING OVEN.

(5) Put the piston assembly in an oven for 1 hour at 120 deg. C (248 deg. F).

WARNING: PUT ON HEAT RESISTANT GLOVES AND BE CAREFUL THE HOT PISTON
ASSEMBLY DOES NOT BURN YOU.

(6) Remove the piston assembly from the oven.

(7) Allow the piston assembly to stand for 2 hours.

(8) Make sure that the length of the piston assembly is not more than 1.487 in.
(37,77 mm).

6. Method 2 - Use Bostik 1777 to bond insulator to piston

WARNING: YOU MUST OBEY THE HEALTH AND SAFETY INSTRUCTIONS OF THE
MANUFACTURER AND YOUR LOCAL INSTRUCTIONS WHEN YOU USE THE
CONSUMABLE MATERIALS.

A. Prepare the adhesive MC JETS, S.A. DE C.V.

(1) Mix the adhesive using three parts of Bostik 1777 to one part of 2-Butanone (Methyl-
Ethyl-Ketone (MEK)) or Ethyl Acetate by weight.

Repair No. 9
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
B. Bonding Procedure

(1) Use a lint free cloth, made moist with 2-Butanone (Methyl-Ethyl-Ketone (MEK)) or
Ethyl Acetate, to clean the mating surfaces of the piston and insulator.

NOTE: During the bonding procedure, a high level of cleanliness of piston and
insulator must be maintained to avoid contamination of prepared and coated
surfaces.

(2) Apply a layer of adhesive to the mating surfaces of the piston and insulator.

(3) Air dry the adhesive to 10 minutes.

(4) Apply a second layer of the adhesive to the mating surfaces of the piston and
insulator.

(5) Air dry the adhesive for 10 minutes.

WARNING: PUT ON HEAT RESISTANT GLOVES WHEN YOU PUT PISTON AND
INSULATOR IN A HOT AIR CIRCULATING OVEN.

(6) Put the piston and insulator in a hot air-circulating oven for 10 minutes at 80 deg. C
(176 deg. F).

WARNING: PUT ON HEAT RESISTANT GLOVES AND BE CAREFUL THE HOT PISTON
AND INSULATOR DOES NOT BURN YOU.

(7) Remove the piston and insulator from the oven after heating.

(8) While the piston and insulator is still hot, mate the coated surfaces and secure tightly
with a suitable clamp.

NOTE: It is recommended a clamping pressure of 3,4 to 13,8 bar (50 to 200 psi) is
used to hold the insulator and piston.

(9) The length of the piston assembly must not be more than 1.487 in. (37,77 mm)
(Ref. Figure R9-601).

WARNING: PUT ON HEAT RESISTANT GLOVES WHEN YOU PUT PISTON ASSEMBLY
IN A HOT AIR CIRCULATING OVEN.

(10) Put the piston assembly in an oven for 1 hour minimum and 2 hours maximum at
150 deg. C (302 deg. F). MC JETS, S.A. DE C.V.
WARNING: PUT ON HEAT RESISTANT GLOVES AND BE CAREFUL THE HOT PISTON
ASSEMBLY DOES NOT BURN YOU.

(11) Remove the piston assembly from the oven.

(12) Allow the piston assembly cool to temperature of 25 deg. C to 20 deg. C

(77 deg. F to 68 deg. F).

Repair No. 9
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(13) Remove the piston assembly from the clamp.

(14) Make sure that the length of the piston assembly is not more than 1.487 in.
(37,77 mm).

Maximum Length of Piston Assembly

Figure R9-601

MC JETS, S.A. DE C.V.

Repair No. 9
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
ASSEMBLY (INCLUDING STORAGE)

1. Special Tools and Materials

A. Special Tools
NOTE: Equivalent alternatives can be used.

Tool No. Description Remarks

2 Key spanner For ring nut

3 Loading and extraction tool For assembly and load checking of
retraction pins
6 Torque spanner 0.5 in. -
square drive
7 Torque spanner adapter Used with Tool No.6 to torque load the
thrust plate attachment bolts
8 Torque spanner 0.375 in. -
square drive
9 Torque spanner adapter Used with Tool No. 8 to torque load the
shuttle valve/blanking plate attachment
bolts
10 Torque spanner adapter Used with Tool No. 8 to torque load the
bleed screw adapters
11 Torque spanner 0.25 in. -
square drive
12 Torque spanner adapter Used with Tool No. 11 to torque load
the bleed screws

B. Materials

NOTE: Refer to the note in Leading Particulars for the temperature limit of hydraulic
fluid.

Material Specification Remarks

Hydraulic Fluid MIL-PRF-5606 Assembly lubricant for sealing rings,

(DEF STAN 91-48) or bleed screw threads and cylinder
MIL-PRF-83282 assembly threads. MC JETS, S.A. DE C.V.
Grease Aeroshell 5 or To aid assembly of external sealing
Praker O-Lube rings on cylinder liner.

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B. Materials (Continued)

Material Specification Remarks

Anti-seize grease SAE AMS2518 Assembly lubricant for ring nut, thrust
plate bolts and blanking plate bolts.
OPT. MIL-PRF-83483
Locking Wire 22 swg to SBAC RS697 To secure bleed screws, torque tube
and DTD189 bolts and cylinder assemblies

2. General

A. Exercise care when fitting rubber sealing rings. Avoid harmful stretching and ensure that,
when fitted, the rings are not trapped or twisted.

B. Absolute cleanliness must be observed during assembly. Protect the friction surfaces
against contamination by hydraulic fluid, oils and greases.

C. Assembly lubricants and compounds should be smeared sparingly on the relevant

components, then wiped off to leave only a fine surface film. There must be no surplus
which might exude into the unit during assembly.

D. Refer to Figure 301, Disassembly, for the item numbers quoted in the following assembly
instructions.

E. Refer to Fits and Clearances for the numerical values of the letters quoted in the following
instructions.

3. Assembly Procedure

A. Locate cylinder block (390) on torque tube assembly (460).

B. Apply a film of the specified grease to the torque tube threads. Fit ring nut (380) and,
using special tool (Tool Item No. 2), fully tighten ring nut (380).

C. Slacken the ring nut sufficient to align the locking holes in ring nut (380) and torque
tube (460).

D. Fit locking pin (370) and split pin (360).

E. Lubricate sealing rings (350) with the specified lubricant and fit sealing rings (350) to the
external grooves of cylinder liners (340). MC JETS, S.A. DE C.V.

F. Lubricate sealing rings (320) and back-up rings (330) with hydraulic fluid and fit sealing
rings (320) and back-up rings (330) to the grooves in the bores of the cylinder liners
(340).

G. Locate a retraction pin (310) in the recess in the top of each cylinder liner (340).

H. Assemble the block and compression tube to special tool (Tool Item No. 3).

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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
I. Assemble the internal components of each piston as follows:

(1) Fit a friction bush (300), shims (295) and spacer (290) in guide
(280). Locate guide (280), spring (270), shim (265) and retaining
washer (260) in piston (240).

NOTE: End float of spacer (290) in guide (280) must be reduced to

a minimum by fitting shims (295) as required between spacer
(290) and friction bush (300). Check that spacer (290) is
flush with the face of guide (280).

(2) Position a circlip (250) over the compression tube of special tool
(Tool Item No. 3). Fit the piston components to the special tool as
illustrated in Figure 302.

CAUTION: THE BOTTOM HALF OF THE WIRE CIRCLIP MUST BE ENGAGED IN THE
PISTON GROOVE, THEN EACH SIDE IN TURN TO ENSURE THAT THE
CIRCLIP ENDS ARE FINALLY LOCATED IN THE PISTON RELIEF CUT-OUT.
FAILURE TO OBSERVE THIS PRECAUTION WILL MAKE SUBSEQUENT
REMOVAL OF CIRCLIP EXTREMELY DIFFICULT.

(3) Rotate the T bar of special tool (Tool Item No. 3) to compress
spring (270) until circlip (250) can be located in the piston
groove with circlip ends adjacent to the cut-out as illustrated
below.

MC JETS, S.A. DE C.V.

Piston Relief Cut-Out

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 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
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MC JETS, S.A. DE C.V.

Cylinder Liner Assembly and Load Checking

Figure 701
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J. Assemble piston assembly (225) to each cylinder liner (340) as follows:

(1) Remove the block and compression tube from special tool (Tool Item No. 3) and fit
cylinder liner (340) and piston assembly (225) as illustrated in
Figure 701, Location A.

(2) Rotate the T bar of special tool (Tool Item No. 3) to push piston (240) fully home in
cylinder liner (340).

K. Load and check each retraction pin as follows:

(1) Ensure the load checking device is primed and bled.

(2) Fit the assembled cylinder liner and piston assembly to special tool
(Tool item No. 3) as illustrated in Figure 701, Location B.

(3) Rotate the T bar to pull the piston from the cylinder liner. As soon as the friction
bush starts to move over the retraction pin, stop turning, and allow the pressure
indicated on the gauge to settle. The pressure must be within the limits of M Ibf/in2
Pins which fail this test must be checked as detailed in sub-para. L.

(4) After satisfactory checking, push the piston fully home into the liner as detailed in
sub-para. J.

L. If retraction pin (310) fails the load check detailed in sub-para. K continues rotating the T
bar to pull the piston assembly from cylinder liner (340). Remove retraction pin (310) from
cylinder liner (340) and check the diameter of the pin. If the pin diameter is not less than
N in. the pin may be regarded as serviceable and friction bush (300) renewed.

NOTE: After renewal of a retraction pin or friction bush a further load check must be
carried out.

M. Load cylinder liner assemblies (220) into cylinder block (390). Secure the assemblies with
circlips (210).

N. Fit wear indicator pin (206) and split pin (204) to the pressure plate assembly (170).

O. Assemble the heat pack to torque tube (460) in the following order:
Pressure plate (170)
Rotor assembly (120)
Double stator (130)
Rotor assembly (120)
Double stator (130) MC JETS, S.A. DE C.V.
Rotor assembly (120)

P. Position thrust plate assembly (70) ensuring that the attachment holes are aligned with
the holes in the torque tube.

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HYDRAULIC PLATE BRAKE, PART NO. AHA1897
Q. Lightly smear the threads of thrust plate attachment bolts (60) with the
specified grease.

R. Fit thrust plate attachment bolts (60). Using special tools (Tool Item
Nos. 6 and 7) tighten in diametrically opposed sequence to the torque
loading specified in Fits and Clearances.

S. Fit a sealing ring (50) to each bleed screw adapter (40). Fit the bleed
screw adapter to cylinder block (390) and, using special tools (Tool
Item Nos. 8 and 10) torque load to the value specified in Fits and
Clearances.

T. Fit bleed screws (30) and, using special tools (Tool Item Nos. 11 and
12) torque load to the value specified in Fits and Clearances.

U. Test the assembled brake unit as detailed in Testing and Fault

Isolation. On completion of testing fit the blanking plate and seal to
the inlet and, using special tools (Tool Item Nos. 8 and 9) torque load
the attachment bolts to the value specified in Fits and Clearances.

V. Wirelock the bleed screw adapters to the cylinder block. Wirelock the
bleed screws to the adapters, wirelock the torque plate attachment bolts
independently to the holes drilled in the circumferential web. The free
ends of the lockwire must be located at the hole in the web, as short as
practicable, and bent back against the web.

4. Storage After Assembly

A. Spare assembled units should be stored in a suitable store room which

provides adequate protection from light and adverse climatic conditions.
The ideal store room temperature is 10 to 21 deg. C (50 to 70 deg. F),
but if this cannot be maintained, the temperature should not exceed 27
deg. C (81 deg. F) and should never be lower than minus 15 deg. C (5
deg. F).

B. Hydraulic units should be stored filled with system fluid. Except for
the filling of hydraulic units contamination of the stored units by
fluids of any description must be avoided.

C. Dunlop advise that units re-assembled with complete new sets of seals
may be stored for a period of up to four years from the date of
reassembly. It is suggested that at the end of this period the complete
set of seals be renewed and the unit re-date marked accordingly.
Relative adjustment to the storage period will need to be considered in
instances where only part of the complete set of seals has been renewed. MC JETS, S.A. DE C.V.

D. Extension of the four year period is at the discretion of the customer

who, before making the decision, must ensure adequate safeguards, such
as sampling checks, confirmation of storage conditions.

E. Where circumstances permit it is recommended that units be periodically

actuated during period of storage.
CO: 9612

32-43-26
Page 706
DAI/3133/50 Rev 1, Jun 19/98
PRINTED IN ENGLAND
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

FITS AND CLEARANCES

1. Heat Pack Data

Brake Double Stator and Pressure Plate

Part No. Rotor Tenon Slot Width
Tenon Shrinkage Inter-
Minimum Gauge Nominal mediate Maximum
Width Clearance P in. (mm) Q in. (mm) R in. (mm)
E in. (mm) F in. (mm)

AHA1897 0.965 0.062 0.656 0.681 0.687

(24,5) (1,57) (16,7) (17,29) (17,45)

Brake Double Stator and Double Stator and Thrust and Pressure
Part No. Pressure Plate Bore Pressure Plate Plate
Clearance
Between To base of Outer Diameter Maximum Dishing
slots slots W in. (mm) G in. (mm)
S in. (mm) T in. (mm)

AHA1897 5.436 6.060 10.468 (265,88) 0.030 (0,762)

(138,0) (154,0)

2. Torque Tube Data

Torque Tube Tenon

Brake Minimum Width
Part No. H in. (mm)

AHA1897 0.560 (14,22)

3. Spring Check Data

MC JETS, S.A. DE C.V.
Under the relevant load the spring must compress to the relevant length
Brake Load Length
Part No. lbf (N) in. (mm)

AHA1897 55.1 - 60.9 0.857 (21,76)

(245,10 - 270,90)

Page 801
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Rev 8, Jul 23/09

COPYRIGHT ” 2009 MEGGITT AIRCRAFT BRAKING SYSTEMS
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE,
BRAKE, PART NO. AHA1897

4. Assembly Data

Brake Friction Check Retraction Pin

Part No. 2 Minimum Diameter
M lbf/in (bar)
N in. (mm)

AHA1897 150/280 0.2005 (5,092)

(10,30/19,20)

5. Torque Loading

IPL Fig.1 Item Torque Loading

Item No.

60 Thrust plate attachment 15 lbf ft (20,34 Nm)

bolt
40 Bleed screw adapter 8 lbf ft (10,84 Nm)
30 Bleed screws 30 lbf in. (3,39 Nm)
Blanking plate 5 lbf ft (6,78 Nm)
attachment bolts

MC JETS, S.A. DE C.V.

32-43-26
CO: 9612

Page 802
Rev 4, 2000/11/03
PRINTED IN ENGLAND
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

SPECIAL TOOLS, FIXTURES AND EQUIPMENT

1. Special Tools and Equipment

NOTE: Alternatives can be used.

Tool Item Tool Description Remarks

No. Part No.

1 A0101795 Tenon wear gauge For stator and pressure plate

tenon slots
2 A0109555 Key spanner For ring nut
3 AM23076 Loading and extraction For assembly and load
AM23104 tool checking of retraction pins
4 AM29366 Clamping plates For reclaiming stator plates
5 SA30088 Alignment fixture Aligning rotors prior to wheel
fitting
6 Norbar SL1 Torque spanner -
0.5 in. square drive
(DSR3278-1)
7 Britool EB500 Torque spanner adapter Used with Item No. 6 to
(DSR2041-3) torque load the thrust plate
attachment bolts
8 Acratrok Torque spanner -
Model A 0.375 in. sq. drive
(DSR1662-4)
9 Britool AB437 Torque spanner adapter Used with Item No. 8 to
(DSR2037-6) torque load the shuttle valve
attachment bolts
10 Britool AB562 Torque spanner adapter Used with Item No. 9 to
(DSR2037-10) torque load bleed screw
adapters
11 Acratork Torque spanner 0.25 in. -
Model Minor square drive
MKIII (DSR1662-2)
MC JETS, S.A. DE C.V.

12 Britool DH344 Torque spanner adapter Used with Item No. 11 to

(DSR2029-8) torque load the bleed screws
Continued...

Page 901
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Rev 10, May 12/14

COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS
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HYDRAULIC PLATE BRAKE, PART NO. AHA1897

Tool Item Tool Description Remarks

No. Part No.

13 SA30089 Resetting tool For resetting friction bushes

with brake in-situ on aircraft

14 A12161 Rotor shrinkage gauge For checking shrinkage of

rotor assemblies

15 A0113718 Adapter assembly For testing brake unit when

shuttle valve is removed
1/4 in. UNF )
28 TPI x 1/2 in. Standard Hexagon Bolt )
long ) Part of Tool Item No. 15
DAS2137-5 Sealing Washer )
A0113385 Adaptor )

16 A0109016 Pressure rig For checking pressure

17 AM21749-1 Riveting set For riveting friction pads

A10298 Fixture )
A0110475 Peening peg )
Part of Tool Item No. 17
A0103583 Pressure plate )
A0105519 Washer )

MC JETS, S.A. DE C.V.

Page 902
32-43-26
CO: 9612

Rev 10, May 12/14

COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

Tenon Wear Gauge A0101795 Loading Extraction Tool AM23076

Load Checking Tool AM23104 Alignment Fixture SA30088

MC JETS, S.A. DE C.V.

Clamping Plates AM29366

Page 903
32-43-26
CO: 9612

Rev 7, Sep 21/07

COPYRIGHT ” 2007 DUNLOP AEROSPACE LIMITED
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

Key Spanner A010955 Resetting Tool SA30089

Rotor Shrinkage Gauge A12161 Riveting Set AM21749/1

MC JETS, S.A. DE C.V.

Adapter Assembly A0113718 Pressure Rig A0109016

Page 904
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CO: 9612

Rev 7, Sep 21/07

COPYRIGHT ” 2007 DUNLOP AEROSPACE LIMITED
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
ILLUSTRATED PARTS LIST

INTRODUCTION

1. Purpose

A. The illustrated part list (IPL) contains the illustrations and the parts
lists for the assembly given in the leading particulars. The parts lists
give the items which can be disassembled, repaired or replaced, and
assembled.

2. To Use this Section

NOTE: The data in paragraph 2.A. thru paragraph 2.F. are included as
necessary in the illustrated parts list (IPL).

A. Figure and Item Column

(1) The figure number at the top left of the column relates the parts
list to the illustration.

(2) The end item number 1A is applicable to the end item that is shown
in the illustration. The items that are changed are shown
immediately after the end item (1B, 1C etc.).

(3) A hyphen (-) before an item number shows that the item is not shown
on the illustration.

(4) The item number sequence is in, as far as possible, the disassembly
sequence of the end item. The sequence is in steps of more than one
to permit, when necessary, more items to be included.

(5) Alpha suffixes, A thru Z (except I and O), are used when it is
necessary to add more items to show:

(a) Special-to-type items.

(b) Service bulletin modifications.

(c) Configuration differences.

(d) Parts that have been made better (non-service bulletin).

(6) Alpha suffixes to the item numbers are not usually shown on the
illustration. This does not apply when the shape and the location MC JETS, S.A. DE C.V.
of the alpha item is not the same as the basic item.

(7) Parts that make a select-from-range group have one (not shown) item
number after the other. This does not apply to the supplied
configuration, or the part number of the smallest part that is
shown.


Page 1001
CO: 9612

Rev 6, Dec 11/03

COPYRIGHT © 2003 DUNLOP AEROSPACE LIMITED
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

B. Part Number Column

(1) The part number column contains the part number which can be:

(a) A part number that is standard such as AGS, MS, AN, LN etc.

(b) The manufacturer’s (Dunlop Aerospace Limited) part number or

its supplier’s part number.

(c) The trade marks of Dunlop Aerospace Limited are: Maxaret, AC,
ACA, ACM, ACO, AH, AHA, AHO, AE, AEA, AEM and AEO.

(d) Trade marks used by Dunlop Aerospace Limited under licence are:
Dunlop and .
(e) The Dunlop stores reference (DSR) or the Dunlop electronic
component (DEC) number when:
- The supplier’s part number is more than fifteen (15)
characters.
- The part number is incorrect (for example the part
number contains a dimension that is a fraction).
- No part number has been given.

C. Airline Part Number Column

(1) This empty column is included for use by the equipment operator.

D. Nomenclature Column

(1) The parts are in a sequence which shows how one part relates to the
other part:

1234567
Assembly or Installation Assembly (RF) number (End Item)
Attaching parts for assembly or installation of RF assembly
***
.Detail parts for assembly
.Subassembly (secondary to lead item)
.Attaching parts for subassembly
***
..Detail parts for subassembly
..Sub-subassembly (secondary to subassembly)
..Attaching parts for sub-subassembly
*** MC JETS, S.A. DE C.V.
...Detail parts for sub-subassembly

NOTE: The words ’or Installation Assembly (RF) number’ is used to

identify a non-procurable group (installation) of parts that
does not make a known assembly.


Page 1002
CO: 9612

Rev 6, Dec 11/03

COPYRIGHT © 2003 DUNLOP AEROSPACE LIMITED
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
(2) The DSR number (when applicable) is included when the part number in the part
number column is not a MABS part number.

(3) The supplier's part number is given in the nomenclature column together with his
vendor code (when a DSR or DEC number is given in the part number column
because the supplier's part number is more than 15 characters or has characters
that are not permitted by the specification ATA100).

(4) The materials from which the part is made and its dimensions are usually specified
together with the supplier's vendor code (when a DSR or DEC number appears in
the part number column due to the lack of a supplier's part number).

(5) Parts which require special handling are identified. For example electrostatic
discharge sensitive electronic components are identified with (ESDS).

(6) Parts Replacement Data

The parts that are interchangeable are identified in the NOMENCLATURE column
of the parts list. The abbreviations used to show those parts that are, or are not,
interchangeable are:
- OPT. The part is optional to and is interchangeable with other parts in
the same item number group (or other item number if designated)
- SUPSD BY The part is replaced by and is not interchangeable with the
item number given
- SUPSDS The part replaces and is not interchangeable with the item
number given
- REPLD BY The part is replaced by and is interchangeable with the item
number given
- REPLS The part replaces and is interchangeable with the item number
given
- ALT The part is not a direct equivalent but is acceptable as an
alternative.

(7) Service Bulletin Incorporation

(a) (PRE-SB XXXX) in the nomenclature column identifies the original

configuration. (POST-SB XXXX) identifies the assemblies and the parts after
the service bulletin modification has been completed.

E. Effectivity Column

(1) Parts identified with an effectivity code (A, B, C etc.) must be used with parts having
the same or no effectivity code. MC JETS, S.A. DE C.V.

Page 1003
32-43-26
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Rev. 9, Nov 13/12

COPYRIGHT  2012 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
F. Units per Assembly Column

(1) The quantity specified is the quantity of a specific-item-numbered part necessary to

build (as applicable) its next higher:
- Its next higher sub-subassembly
- Subassembly
- Assembly or installation level.

(2) AR is given for bulk items, and select-from-range parts that are not shown on the
illustration. The quantity is that necessary for the assembly.

(3) RF shows the part is included in the illustrated parts list for identification only.

3. Vendor Code List

The vendor code numbers are those in:

- The national NATO code for manufacturers (NSCM) H4-1 and H4-2 or
- The USA, Department of Defense, Commercial and Government Entity (CAGE)
Cataloging Handbook H4/H8.

Vendor Code Vendor Address

K1037 Meggitt Aircraft Braking Systems Holbrook Lane

Coventry
CV6 4AA
UK
96906 United States of America
Military Departments Under
Authority of Defence
Standardization Manual 4120 3-M
U1653 Society of British Aerospace Companies Salamanca Square
Ltd (SBAC) 9 Albert Embankment
London
SE1 75P
UK
80205 National Aerospace Standards 1000 Wilson Blvd Suite 1700
Committee Aerospace Industries Arlington
Asscoation of America Inc VA 22209
USA

K7766 British Standards Institution 389 Chisick High Road MC JETS, S.A. DE C.V.
London
W4 4AL
UK

Page 1004
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CO: 9612

Rev. 9, Nov 13/12

COPYRIGHT  2012 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
4. Color Coding of Rotor Segments

NOTES: 1. New segments are marked with colored lines for easy
identification in store.

2. One, two or three lines can be used. Shown in this diagram are
two lines only, positions 1 and 2.

3. The positions of lines and colors used for segments installed in

the brakes of this manual are as shown below.

4. The color code No. given in the left hand column can be used, in
correspondence etc, to identify the color combination shown in
the right hand column.

Identification Colors
Color Segment 1 2
Code No. Part No.

94 AHM9053 Red Yellow

MC JETS, S.A. DE C.V.

Jig-saw Segment and Table

IPL Figure 1

NOTE: Segments other than Jig-saw not applicable.


Page 1005
CO: 9612

Rev 6, Dec 11/03

COPYRIGHT © 2003 DUNLOP AEROSPACE LIMITED
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

MC JETS, S.A. DE C.V.

Brake Unit – Exploded View

IPL Figure 2

Page 1006
32-43-26
CO: 9612

Rev 10, May 12/14

COPYRIGHT  2014 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
ILLUSTRATED PARTS LIST
Fig Item Part Number Airline Nomenclature Eff Units
Stock No. 1 2 3 4 5 6 7 Code per
Assy
2-1 AHA1897 HYDRAULIC PLATE BRAKE RF
30 AGS3049 . SCREW BLEED (K1037) 2
40 AH080553 . ADAPTER BLEED SCREW (K1037) 2
50 DAS2157-3 . RING SEALING (K1037) 2
(Pre-AMDT37763)
-50A DAS2119-5 . RING SEALING (K1037) 2
(Post-AMDT37763)
(Pre-AMDT37863)
-50B DAS2119-3 . RING SEALING (K1037) 2
(Post-AMDT37863)
OPT. M83461-2-903 (96906)
60 AH082821 . BOLT (K1037) 8
-65 AH089881 . HEAT PACK ASSY (K1037) 1
70 AH085003 . . PLATE ASSY THRUST (K1037) 1
80 AH080972-1 . . . RIVET (K1037) 8
90 AH082396 . . . PLATE RIVET (K1037) 8
100 AH083829-6 . . . PAD ASSY (K1037) 8
105 AH083326-7 . . . PIECE PACKING (K1037) 8
110 AHM7127 . . . PLATE THRUST (K1037) 1
120 AHM9053 . . SEGMENT ROTOR (K1037) 18
130 AH085004 . . STATOR ASSY DOUBLE (K1037) 2
140 AH080972-1 . . . RIVET (K1037) 8
USE AH080972-4 ON GALEX
150 AH083829-6 . . . PAD ASSY (K1037) 16
155 AH083327-4 . . . PIECE PACKING (K1037) 8
160 AHM7151 . . . PLATE STATOR (K1037) 1
170 AH089880 . . PLATE ASSY PRESSURE (K1037) 1
180 AH080972-3 . . . RIVET (K1037) 8
190 AH083829-6 . . . PAD ASSY (K1037) 8
195 AH083326-7 . . . PIECE PACKING (K1037) 8
197 AH089040 . . . INDICATOR PIN RETAINER (K1037) 2
200 AHM8974 . . . PLATE PRESSURE (K1037) 1
204 MS24665-134 . PIN SPLIT (K1037) 2
DSR57851-1308 (K1037) MC JETS, S.A. DE C.V.
206 AH089645 . PIN INDICATOR (K1037) 2
210 DSR51657-1030 . CIRCLIP (K1037) 5
OPT DSR1961-16 (K1037)
220 AH088413 . LINER ASSY CYLINDER (K1037) 5
225 AH088412 . . PISTON ASSY (K1037) 1
230 AH083149 . . . INSULATOR (K1037) 1
- ITEM NOT ILLUSTRATED

Page 1007
32-43-26
CO: 9612

Rev. 9, Nov 13/12

COPYRIGHT  2012 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897
ILLUSTRATED PARTS LIST
Fig Item Part Number Airline Nomenclature Eff Units
Stock No. 1 2 3 4 5 6 7 Code per
Assy
240 AH088411 . . . PISTON (K1037) 1
250 AH084479 . . CIRCLIP WIRE (K1037) 1
260 AH084478 . . WASHER RETAINING (K1037) 1
265 AH089075 . . SHIM (K1037) AR
-267 AH088784 . . SHIM (K1037) AR
270 AH088449 . . SPRING (K1037) 1
280 AH088417 . . GUIDE (K1037) 1
290 AH088448 . . SPACER (K1037) 1
295 AH038251 . . SHIM (K1037) AR
300 AH081710 . . BUSH FRICTION (K1037) 1
310 AH088420 . . PIN RETRACTION (K1037) 1
320 DAS2158-20 . . RING SEALING (K1037) 1
(Pre-AMDT37763)
-320A DAS2137-20 . . RING SEALING (K1037) 1
(Post-AMDT37763)
OPT. M83461-1-215 (96906)
330 DAS2233-20 . . RING BACK-UP (K1037) 1
MOD. M10631(0)
OPT. MS27595-215 (96906)
340 AHM8313 . . LINER CYLINDER (K1037) 1
350 DAS2206-9 . RING SEALING (K1037) 10
(Pre-AMDT37763)
-350A DAS2118-9 . RING SEALING (K1037) 10
(Post-AMDT37763)
OPT.M83461-1-125 (96906)
360 BSSP90B3 . PIN SPLIT (K7766) 1
DSR231-2 (K1037)
OPT. MS24665-69 (96906)
370 AH037275 . PIN LOCKING (K1037) 1
380 AH083148 . NUT RING (K1037) 1
390 AH089791 . BLOCK ASSY CYLINDER (K1037) 1
(MAJOR)
391 DSR213-1 . . BOLT (K1037) 2
BSA104-1/2A (K7766)
392 DSR4462-1012 . . WASHER (K1037) 2 MC JETS, S.A. DE C.V.
NAS1149C0363R (80205)
393 AH089646 . . BRACKET INDICATOR (K1037) 2
-394 AS6733-17 . . INSER WIRE THREAD (U1653) 2
DSR861-2 (K1037)
OPT. MS124696 (96906)
-395 DSR1002-3 . . INSERT WIRE THREAD (K1037) 2
OPT. MS21209-F4-20 (96906)
- ITEM NOT ILLUSTRATED

Page 1008
32-43-26
CO: 9612

Rev. 9, Nov 13/12

COPYRIGHT  2012 MEGGITT AIRCRAFT BRAKING SYSTEMS
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COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

ILLUSTRATED PARTS LIST

Units
Airline Eff
Fig Item Part Number Nomenclature per
Stock No. Code
1234567 Assy
400 DSR894-2 . . SCREW TYPE (K1037) 16
U 00 DIA X 3/16 LG
410 AH035273 . . PLATE REFERENCE (K1037) 1
420 AH035274 . . PLATE REFERENCE (K1037) 1
430 AH081282 . . PLATE REFERENCE (K1037) 1
440 AH081283 . . PLATE REFERENCE (K1037) 1
450 AHM9054 . . BLOCK ASSY CYLINDER (K1037) 1
(MINOR)
460 AH088453 . TUBE ASSY TORQUE (K1037) 1
470 AH083343 . . RIVET (K1037) 2
480 AH083147 . . COLLAR LOCATING (K1037) 2
482 AH088444 . . RIVET (K1037) 1
490 AH43955 . . TUBE TORQUE (K1037) 1
TRANSIT ITEMS
-500 AH082174 . BOLT (K1037) 2
(Pre-MOD M10756(0))
SUPSD BY Item 500A
-500A DSR2389-1 . BOLT (K1037) 2
(Post-MOD M10756(0))
SUPSDS Item 500
-510 AH081864 . PLATE BLANKING (K1037) 1
(Pre-MOD M10756(0))
SUPSD BY Item 510A
-510A AH089679 . PLATE BLANKING (K1037) 1
(Post-MOD M10756(0))
SUPSDS Item 510
-520 DAS2158-5 . RING SEALING (K1037) 1
(Pre-DCD20500, Iss 62)
REPLD BY Item 520A
-520A DAS2137-5 . RING SEALING (K1037) 1
(Post-DCD20500, Iss 62)
REPLS Item 520
(Pre-MOD M10756(0)) MC JETS, S.A. DE C.V.
SUPSD BY Item 530
-530 AH089680 . SEALING STRIP (K1037) 1
(Post-MOD M10756(0))
SUPSDS Item 520A
-540 DAA05360-01 . HEATPACK SPARES (K1037)
ORDERING KIT
AH083829-6 . . PAD ASSY (K1037) 48

- ITEM NOT ILLUSTRATED

Page 1009
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Rev 8, Jul 23/09

COPYRIGHT ” 2009 MEGGITT AIRCRAFT BRAKING SYSTEMS
 EMAIL: jbaeza@redwings.aero
COMPONENT MAINTENANCE MANUAL
HYDRAULIC PLATE BRAKE, PART NO. AHA1897

ILLUSTRATED PARTS LIST

Units
Airline Eff
Fig Item Part Number Nomenclature per
Stock No. Code
1234567 Assy
AHM9053 . . SEGMENT ROTOR (K1037) 18
AH080972-3 . . RIVET (NON ORGANIC PAD) (K1037) 8
AH080972-1 . . RIVET (NON ORGANIC PAD) (K1037) 8
AH080972-4 . . RIVET (NON ORGANIC PAD) (K1037) 16
AH089645 . . PIN INDICATOR (K1037) 2

SPECIAL FIT ONLY

AH54388 . INSTALLATION SLUSH GUARD(K1037) 1

AH084674 . . CIRCLIP (K1037) 5
AHM8396 . . GUARD PORT INNER (K1037) 1
STBD OUTER
AHM8395 . . GUARD PORT OUTER (K1037) 1
STBD INNER

MC JETS, S.A. DE C.V.

- ITEM NOT ILLUSTRATED

Page 1010
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COPYRIGHT ” 2009 MEGGITT AIRCRAFT BRAKING SYSTEMS