aircraft maintenance manual

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NOTE

Please be aware that the material in this manual does not strictlyfollow the ATA code format. In order to catalog them according to ATAstandards, ATP has recoded them. Please see the example(s) below.

EXAM PLE

Manufactu rers ATP Coding TopicCoding

20-95-00 20-95-00 00 CONSUMABLE MATERIALSAND APPROVED SUPPLIERS

20-95-11 20-95.00 11 GREASE AND LUBRICANTS20-95-101 20.95.00 101 FLUIDS AND OILS

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ATP Grid Index to Manufacturers Publications:

Raytheon Aircraft Co.125 Series 1-1000, Hawker 800,1000,800XPStandard Practices Manual

Section Topic

General Information

Title PageList of Chapters (Table of Contents)Manufacturers IntroductionRecord of RevisionsRecord of Temporary RevisionsLetter of Transmittal (Highlights of Changes)List of Effective PagesExisting/Previous ATA Numbers

Airframe Systems

20.00.00 Standard Practices Airframe20.09.00 20 Torque Loading Maintenance Practices20.09.00 21 Retention of W S Retaining Rings-Maint Practices20.09.00 23 Reuse of Self-Locking Nuts-Maintenance Practices20.09.00 41 Component Locking Maintenance Practices20.09.00 91 Flaring of Stainless Steel Tubes Maint Practices20.09.00 141 Countersunk Head Bolts-Maintenance Practices20.10.00 08 Application of Alorcom 1200 Epoxide Primer20.10.00 31 Control Cables (Examination Rejection Criteria)20.10.00 32 Control Cables (Corrosion Protection)20.10.00 33 Stripping of Pain Maintenance Practices20.10.00 34 Chemical Removal of Polysulphide (PRC) Sealants20.10.00 40 Vacu-Blasting with Dry Alumina Grit20.10.00 50 Wiring Procedures and Repair20.10.00 Temporary Revision No. 20-320.10.00 75 Application of Sodium Alginate Release Agent20.10.00 228 Application of Urethane Finish to External Surface

06/22/2006 Copyright Aircraft Technical Publishers Page 1 of 3BS 0900 ZP

Section Topic

20.10.00 354 Leak Testing Fluid20.10.00 447 Sealing Compound Flexible Seal Applications20.10.00 481 Electrically Conducting Jointing Compounds20.10.00 482 Application of Acid Resisting Paint20.10.00 499 Sealing of Perspex, Laminated Glass Windows Pnls20.10.00 560 Renovation of Furnishing Materials20.10.00 811 Polish Aircraft Skins (External)20.10.00 1001 Sealing Intgrl Fuel Tnks with Polysulfide Cmpnds20.10.00 1002 Sealing Prsr Cbns Areas Outside Intgrl Fuel Tnks20.10.00 1009 Form-in-Place Seals for Weatherproofing20.10.00 3003 Aerodynamic Smoothing Sealant20.10.00 3005 High Temperature Sealants (Silcoset and Silastic)20.10.00 3008 Metal Filled Epoxies for Gap Filling20.10.00 3527 Appl of Cold Curing Epxy Primer to Int Ext Srfcs20.10.00 3528 Application Flexible/Permeable Finish Intrnl Srfcs20.10.00 3534 App of Polyurthne Fin Enml for Overcoating Sealnts20.10.00 3537 Applctn of Antistatic Paint to Composite Materials20.10.00 4005 Bonding Silicone Rubbers20.10.00 4007 Bonding Rubber and P.T.F.E. to Perspex or Metal20.10.00 4011 Bonding w/Epoxy Adhesives for Non Structural Parts20.10.00 4012 Rubber Bonding Adhesive20.10.00 4014 Bonding with Contact Adhesive20.10.00 4016 Bonding with Scotch-Seal Metal Sealant 208420.10.00 4501 Shrink Fitting of Bolts. Bushes, Pins, etc.20.10.00 4507 Locking of Threads with Anaerobic Adhesive20.10;.00 4553 Retention of Bushes Bearings by Liquid Sealant20.10.00 5016 Electrical Bonding20.10.00 9053 Degreasing of Metallic Materials20.101.00 9070 Preparation of Rubber Surfaces for Bonding20.11..00 1040 Very High Temperature Sealants20.11..00 1041 Precipitation Static (P-Static) Test20.95.00 00 Consumable Materials-Approved Suppliers20.95.00 11 Consumable Materials-Grease and Lubricants20.95.00 101 Consumable Materials-Fluids and Oils20.95.00 201 Cleaning Agents, Paint Strippers Release Agents20.95.00 301 Adhesives, Jointing and Sealing Compounds20.95.00 401 Enamels, Lacquers, Paint, Primers and Varnishes20.95.00 501 Chemical and Electro-Chemical Surface Finishes20.95.00 601 Consumable Materials-Miscell aneous Materials

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Secti on Topi c

End of Index

06/22/2006 Copyright Aircraft Technical Publishers Page 3 of 3

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NI FG.

INTRO

Raytheon Aircraft Company

111)1,

25 Series 000,Hawker 800, 1000, 800XP 850XP

Aircraft Maintenance Manual

Chapter 20Standard Practices Airframe

Copyright O 2006 Raytheon Aircraft Company. All rights reserved.

PIN: AMM 125/H-20 Rev: 7Issued: April 1999 Dated: March 2006

Published byRAYTHEON AIRCRAFT COMPANY

P.O. Box 85Wichita, Kansas67201 -0085 USA

The export of these commodities, technology or software are subject to the US ExportAdministration Regulations. Diversion contrary to US law is prohibited. For guidance on exportcontrol requirements, contact the Commerce Departments Bureau of Export Administration at 202-482-4811 or visit the VS Department of Commerce website.

RlyWKon ~mhr.tWULAircraft Company General AviationGAMA Manufacturers Assoclatlon

RECORD OF REVISIONS

MFG REVNO DESCRIPTION ISSUEDATE ATPREVDA~ INSERTED BY

1 See Highlights 1211/99 5/11100 ATP/MG

2 See Highlights 6/7/01 ATP/IB

3 See Highlights 6/02 10/24/02 ATP/MB

4 See Highlights 6/03 8114/03 ATPIJB

5 See Highlights 6/04 8/4104 ATP/JSF

6 See Highlights 6/05 7/15/05 ATP/JSF

7 See Highlights 3/06 4/26/06 ATP/RCL

Rayrheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

RECORD OP REVISIONS (NORMAL)

Revisions embodied in this manual, which have been issued by an approval authorization other thanRaytheon Aircraft Company must be recorded on separate record sheets.

Revision No. RevisionDate \nsertionDate Inserted By

112/99 5-11-00 ATP/MG

2 01/01/01 06/07/01 ATP/IB

0 10/24/02 ATP

4 ATP/JB6/03 8/14/03

6/04 8/4/04 ATP/JSF6 6/05 7/15/05 I~rPIJSF

7 3/06 4/26/06 ATP/RCL

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Record of RevisionsPage 1

Apr. 99

Ray~heon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

Revision No Revision Date Insertion Date Inserted By

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Record of RevisionsPage 2

Apr. 99

RECORD OF TEMPORARY REVISIONS

TEMP ATP REV INSERT DATE REV REMOVEREV NO DESCRIPTION ISSUE DATE DATE BY REMOVED INCOR BY

20-1 20-95-301:10 &16 3/1100 5/11/00 ATP/MG 6/7/01 2 ATPIIB

20-2 20-95-00.15, 20-95-11:7 5105 7/1 5/05 ATP/JSF 4/26/06 7 ATP/RCL

20-3 20-1 0-50:201 5106 7/5106 ATP/VP

Rayrheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

j RECORD OF TEMPOAARYREVISIONSRevisions embodied in this manual, which have been issued by an approved authorization other thanRaytheon Aircraft Company, must be recorded on separate record sheets.

LOT No. TR No. Affecting Inserted Removed

Part Page Inserted Date Cancelled Dateby by

20-1 20.95.301 10 16 ATP/MG 5-11-00 ATP/IR 6/07/01to-2 Z~TP/JTjF 7/! 5/1)5 ATP/RCT 4-/2(j/06

zo-~ 20-10-50 201 ATP/VP 7/5/0h

Record of Temporary RevisionsPage 1

Apr. 99

Ralrheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

LOT No. TR No. Affecting Inserted Removed

Part Page Inserted Date Cancelled Dateby by

9

Record of Temporary RevisionsPage 2Apr. 99

RBYtheOn Aircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

(P/N: AMM 125/H-20)TEMPORARY REVISION TR 20-3LETTER OF TRANSMITTAL No.03

Raytheon Aircraft CompanyRO. Box 85

WichitaKansas 67201

U.S.A

1. Reasonfor issue

Lugs on UAM100 fuses are breaking due to incorrect installation.

2. Instructions Holders of Printed Manuals

(1) Insert Temporary Revision as detailed below.

(2) Record the incorporation of this Temporary Revision on the RECORD OF TEMPORARY REVISIONSsheet at the front of the manual.

(3) Retain this Letter of Transmittal and file immediately following RECORD OF TEMPORARYREVISIONS sheet.

TR No. Position Instructions

20-3 Facing Chapter 20-10-50, page block 201 INSERT

3. Action

In place of 20-10-50 page block 201 read this TR.

4. List Of Current Temporary Revisions (Manual at Revision 7).

NOTE: Temporary Revisions are only to be removed from the manual when specific instructions aregiven in a Letter of Transmittal issued with a NORMAL or TEMPORARY Revision.

TR No. Position Issued with Transmittal No.

20-3 Facing Chapter 20-10-50, page block 201 03

Letter of TransmittalPage 1 of 1

May.05

RBytheOn Airrraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

Raytheon Aircraft CompanyP.O. Box 85

Wichita

Kansas 67201USA

125 Series 1-1000Hawker 800, 800XP, 850XP 1000

P/N: AMM 125/H-20

LETTER OF TRANSMITTAL REVISION 7

1. HOLDERS OF PRINTED MANUALS

(1) Make sure that Revision 6 has been incorporated.

(2) Remove and destroy Temporary Revisions detailed for removal at Paragraph 4 of this transmittal andcancel any entries for these temporary revisions on the RECORD OF TEMPORARY REVISIONSsheet at the front of this manual.

(3) Insert the revision pages in numerical sequence, removing and destroying the existing pagesreplaced by the revised pages as instructed in Paragraph 3 of this transmittal.

(4) Record the incorporation of this revision on the RECORD OF REVISION (NORMAL) sheet at thefront of this manual.

(5) Retain this Letter of Transmittal and file at the front of this manual.

2. HIGHLIGHTS

NOTE: All topics included in this revision have been re-issued and dated Mar.OG

Ch-Se-Su Description of change

TITLE PAGE Model 850XP added to Series header. Date and Revision No. revised.Area code revised to add -0085. Export statement revised.

INTRO-LOEP Page Dates revised.

INTRODUCTION Reissued. New format and content added.

20-LOEP Reformatted and revised.


Mar.OG

Raytheon Aircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME


CHAPTERS:

20-10-5016 MAINTENANCE PRACTICES Topic reformatted. Paragraph 1. revised to readInSormation (was General). NOTE added reference 20-10-50, 201 and AMMChapter 24, Electrical Power.

20-95-00 CONSUMABLE MATERIALS APPROVED SUPPLIERS Paragraph 1.Information revised, reference to website for Manufacturers and Federal Codesadded. Page 16, NA.117 and NA.118, new suppliers added (TR 20-2incorporated). NA.119 new supplier added.Page 18, UK.12, format revised, "Obsolete" replaced by NA.9 (transferred fromSuppliers column).

20-95-11 CONSUMABLE MATERIALS GREASES AND LUBRICANTS Page 7, Item 092,new material introduced (TR 20-2 incorporated).

20-95-301 CONSUMABLE MATERIALS ADHESIVES, JOINTING AND SEALINGCOMPOUNDS Topic reformatted. Paragraph 1. Information heading added andsubsequent headings re-numbered.Page 9, Item 361, alternative sealants introduced.Page 10, Item 367, suppliers code revised to UK.10 (was NA.10), Item 369,suppliers code revised to UK.106 (was UK.25) and Item 371(a), specification MILspec. revised.

Page 16, Item 330A, specification MIL spec. revised. Item 331A, specificationMIL spec. revised and alternative introduced.

Page 18, Item 350A, Item 351A and Item 352A, new materials introduced.

20-95-401 CONSUMABLE MATERIALS ENAMELS, LACQUERS, PAINTS, PRIMERS ANDVARNISHES Topic reformatted. Paragraph 1. Information heading added andsubsequent headings re-numbered.Page 3, Item 440, material and specification revised, statement added to remarks.Page 4, Item 466, NOTE revised.

20-95-601 CONSUMABLE MATERIALS, MISCELLANEOUS MATERIALSPage 4, Item 643, specification revised.Page 8, Item 606A and Item 607A, new material introduced.


Mar.OG

Raytheon Aircraft tompany125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

3. INSTRUCTIONS FOR INCORPORATING THIS REVISION

Remove Insert RemoveCh-Se-Su

Page(s) Page(s) TRTitle Page 1/2 1/2

Intro- LOEP 1 1

Introduction 1 thru 4 1 thru 5

LOEP 1 thru 4 1/2

20-1 0-5016 201 thru 201 thru

231 229

20-95-00 1 thru 29 1 thru 30 20-2

20-95-11 1 thru 7 1 thru 7 20-2

20-95-301 1 thru 19 1 thru 18

20-95-401 1 thru 8 1 thru 8

20-95-601 1 thru 8 1 thru 8

4. TEMPORARY REVISIONDATA

TR 20-2 incorporated at this revision.


Mar.OG

RgJaPleOn Aircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

Raytheon Aircraft CompanyP.O. Box 85

Wichita

Kansas 67201USA

125 Series 1-1000Hawker800,1000,800XP

P/N: AMM 125/H-20

LETTER OF TRANSNIITTAL REVISION 6

1. HOLDERSOFPRINTED MANUALS

(1) Make sure that Revision 5 has been incorporated.

(2) Remove and destroy Temporary Revisions detailed for removal at Paragraph 4 of this transmittal andcancel any entries for these temporary revisions on the RECORD OF TEMPORARY REVISIONSsheet at the front of this manual.

NOTE: Do not remove TR 20-2 tissued May 05) at this time. TR 20-2 will be incorporated atPermanent Revision No. 7

(3) Insert the revision pages in numerical sequence, removing and destroying the existing pagesreplaced by the revised pages as instructed in Paragraph 3 of this transmittal.

(4) Record the incorporation of this revision on the RECORD OF REVISION (NORMAL) sheet at thefront of this manual.

(5) Retain this Letter of Transmittal and file at the front of this manual.

2. HIGHLIGHTS

NOTE: All topics included in this revision have been re-issued and dated Jun.D5.


TITLE PAGE Revision No. and Date revised.

INTRO-LOEP Page dates revised.

INTRODUCTION Paragraph 1.A and 1.C. website addresses revised.

LOEP Page dates revised.

CONTENTS New topics 20-09-41 (Component locking) and 20-11-1041 (Precipitation Static(P-Static)) added.


Jun.05

Raytheon Aircraft Company125lHAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME


Existing/previous New topics 20-09-41 and 20-11-1041 added.ATA numbers

CHAPTERS

20-09-41 New topic introduced MAINTENANCE PRACTICES.

20-10-50 MAINTENANCE PRACTICES Paragraph 1.title revised to INFORMATION.Paragraph 2.B. (2) (a) (requirement to check splices after a set period) deleted.

20-11-1041 New topic introduced MAINTENANCE PRACTICES.

20-95-00 CONSUMABLE MATERIALS, APPROVED SUPPLIERS List revised. Newsuppliers NA.114, NA.115 and NA.116 added.

20-95-11 CONSUMABLE MATERIALS GREASES AND LUBRICANTSItem 054, MIL SPEC. revised.

Items 089 and 090, material name revised to Corrosion Preventive Compound(was Rust inhibitor).

Item 091 (Petrolatum, Lubricant) introduced.

20-95-101 CONSUMABLE MATERIALS FLUIDS AND OILSItem 101, TKS Fluid. Specifications revised and new suppliers code NA. 114added.

Item 139, Fluid, refrigerant, mixing details added.

Item 140, Oil, refrigerant, supplier details revised and mixing details added.

Item 147, Fuel, engine. Material name and specification revised. Reference toAMM Chapter 12, FUEL SYSTEM SERVICING added to remarks column.

Item 148, Fuel, engine. Material name and specification revised. Reference toAMM Chapter 12, FUEL SYSTEM SERVICING added to remarks column.

Item 151, Oil, general purpose light lubricating. New oil added.

Item 152, Fuel, engine Jet A introduced.


Jun.05


3. INSTRUCTIONS FOR INCORPORATING THIS REVISION

Remove Insert RemoveCh-Se-Su

Page(s) Page(s) TRTitle Page 1/2 1/2

Intro-LOEP 1 1

Introduction 1 thru 4 1 thru 4

LOEP 1 thru 4 1 thru 4

CONTENTS 1 thru 4 1 thru 4

20 ATA-REF 1 thru 3 1 thru 4

20-09-41 201 thru

204

20-1 0-50 201 thru 201 thru204 204

20-11-1041 201 thru

204

20-95-00 1 thru 29 1 thru 29

NOTE: Do notremove TR20-2, Page i.

20-95-11 1 thru 7 1 thru 7

NOTE: Donotremove TR20-~ PageP.

25-95-101 1 thru 5 1 thru 5

4. TEMPORARY REVISION DATA

TR 20-2 tissued May 05).

NOTE: Donotremove TR20-2atthistime


Jun.05

Ilaylheon Aircraft CompanyI25/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

(P/N: AMM 125/H-20)TEMPORARY REVISION TR 20-2LETTER OF TRANSMITTAL No.02

Raytheon Aircraft CompanyP.O. Box 85,

WichitaKansas 67201

U.S.A

1. Reasonfor issue

TR 20-2 introduces two new US suppliers (NA.117 and NA.118) to Chapter 20-95-00 and a new CorrosionPreventative Lubricant (Item 092) to Chapter 20-95-11.

2. Instructions Holders of Printed Manuals

(1) Insert Temporary Revision as detailed below.

(2) Record the incorporation of this Temporary Revision on the RECORD OF TEMPORARY REVISIONSsheet at the front of the manual.

(3) Retain this Letter of Transmittal and file immediately following RECORD OF TEMPORARYREVISIONS sheet.

TR No. Position Instructions

20-2 TR page 1, facing Chapter 20-95-00, page 15. INSERTTR page 2, facing Chapter 20-95-11, page 7. INSERT

3. Action

In addition to page 15 (20-95-00) read page 1 of this TR.

In place of page 7 (20-95-11) read page 2 of this TR.

4. List Of Current Temporary Revisions (Manual at Revision 5).

NOTE: Temporary Revisions are only to be removed from the manual when specific instructions aregiven in a Letter of Transmittal issued with a NORMAL or TEMPORARY Revision.

TR No. Position Issued with Transmittal No.

20-2 TR page 1, facing Chapter 20-95-00, page 15. 02TR page 2, facing Chapter 20-95-11, page 7.


May 05

Ray~heon Aircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

LIST OF EFFECTIVE PAGES

CH-SE-SU PAGE DATE CH-SE-SU PAGE DATE

CONTENTS 1 thru 4 Jun.05 20-10-560 201 thru 209 Jun.03

20 ATA-REF. 1 thru 4 Jun.05 20-10-811 201/202 Jun.04

20-00-00 1 Jun.02 20-10-1001 201 thru 211 Jun.03

20-09-20 201 thru 207 Jun.04 20-10-1002 201 thru 211 Jun.03

20-09-21 201 thru 211 Jan.2001 20-10-1009 201 thru 206 Jun.04

20-09-23 201/202 Jan.2001 20-10-3003 201 thru 204 Jun.02

20-09-41 201 thru 204 Jun.OS 20-10-3005 201 thru 204 Jun.03

20-09-91 201 thru 204 Dec.99 20-10-3008 201 thru 203 Jun.02

20-09-141 201/202 Dec.99 20-10-3527 201 thru 209 Jun.03

20-10-08 201 thru 203 Jun.03 20-10-3528 201 thru 206 Jun.02

20-10-31 201 thru 207 Jun.04 20-10-3534 201 thru 203 Jun.03

20-10-32 201/202 Jan.2001 20-10-3537 201 thru 207 Jun.02

20-10-33 201 thru 204 Jun.OS 20-10-4005 201 thru 204 Jun.02

20-10-34 201/202 Jan.2001 20-10-4007 201 thru 203 Jun.02

20-10-40 201 thru 204 Jun.03 20-10-4011 201 thru 204 Jun.02

20-10-50 1 thru 8 Jun.02 20-10-4012 201 thru 204 Jun.02

201 thru 204 Jun.0520-10-4014 201 thru 204 Jun.02

20-1 0-75 201/202 Jan.200120-10-4016 201 thru 203 Jun.OS

20-10-228 201 thru 206 Jun.OLt20-10-4501 201/202 Jan.2001

20-10-354 201 thru 203 Jun.04 203 thru 205 Dec.99

20-10-447 201 thru 204 Jun.02 20-10-4507 201 thru 204 Jun.02

20-1 0-481 201 thru 203 Jun.02 20-10-4553 201 thru 203 Jan.2001

20-10-482 201 thru 203 Jun.02 20-10-5016 201 thru 229 Mar.OG

20-10-499 201 thru 204 Jun.02 20-10-9053 201 thru 203 Jun.04

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RaYtaeOn Aircraft Company1251HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

CH-SE-SU PAGE DATE

20-10-9070 201 thru 204 Jun.04

20-11-1040 201 thru 203 Jun.02

20-11-1041 201 thru 204 Jun.0S

20-95-00 1 thru 30 Mar.OG

20-95-11 1 thru 7 Mar.OG

20-95-101 1 thru 5 Jun.05

20-95-201 1 thru 7 Jun.04

20-95-301 1 thru 18 Mar.OG

20-95-401 1 thru 8 Mar.OG

20-95-501 1/2 Jun.04

20-95-601 1 thru 8 Mar.0G

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RCIYHI(WDII Aircraft Company1251HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

TABLE OF CONTENTS

NOTE: To locate topics that previously existed in an AM~I and may still be referred to, refer to the %xisting/previous ATA numbers table" immediately following this TOC.

Subject Ch-Se-Su Page

STANDARD PRACTICES AIRFRAME

GENERAL 20-00-00

Description 1

TORQUE LOADING 20-09-20Maintenance Practices 201

RETENTION OF BEARINGS BY W AND S RETAINING RINGS 20-09-21Maintenance Practices 201

REUSE OF SELF-LOCKING NUTS 20-09-23Maintenance Practices 201

COMPONENT LOCKING 20-09-41

Maintenance Practices 201

FLARING OF STAINLESS STEEL TUBES 20-09-91


COUNTERSUNK HEAD BOLTS 20-09-141


APPLICATION OF ALOCROM 1200 (ALODINE 1200) 20-10-08Maintenance Practices 201

CONTROL CABLES (EXAMINATION AND REJECTION CRITERIA) 20-10-31Maintenance Practices 201

CONTROL CABLE (CORROSION PROTECTION) 20-10-32Maintenance Practices 201

STRIPPING OF PAINT 20-10-33


CHEMICAL REMOVAL OF POLYSULPHIDE (Pr-tC) SEALANTS 20-10-34Maintenance Practices 201

VACU-BLASTING WITH DRY ALUMINA GRIT 20-10-40


WIRING PROCEDURES AND REPAIR 20-10-50

Description and Operation 1Maintenance Practices 201

20-CONTENTSPage 1Jun.05

Raytheon Asrcralt Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME


STANDARD PRACTICES AIRFRAME continued

APPLICATION OF SODIUM ALGINATE RELEASE AGENT 20-10-75Maintenance Practices 201

APPLICATION OF URETHANE FINISH TO EXTERNAL SURFACES 20-10-228Maintenance Practices 201

LEAK TESTING FLUID 20-10-354Maintenance Practices 201

LEAK TESTING FLUID (SHERLOCK) 20-10-355Topic Deleted (Data transferred to Topic 20-10-354

SEALING COMPOUND FLEXIBLE SEAL APPLICATIONS 20-10-447Maintenance Practices 201

ELECTRICALLY CONDUCTING JOINTING COMPOUNDS 20-10-481Maintenance Practices 201

APPLICATION OF ACID RESISTING PAINT 20-10-482Maintenance Practices 201

SEALING OF PERSPEX, LAMINATED GLASS WINDOWS AND PANELS 20-10-499Maintenance Practices 201

RENOVATION OF FURNISHING MATERIALS 20-10-560Maintenance Practices 201

POLISH AIRCRAFT SKINS (EXTERNAL) 20-10-811Maintenance Practices 201

SEALING OF INTEGRAL FUEL TANKS WITHPOLYSULFIDE TYPE COMPOUNDS 20-10-1001


SEALING OF PRESSURE CABINS AND AREAS OUTSIDE INTEGRALFUEL TANKS WITH POLYSULFIDE TYPE COMPOUNDS 20-10-1002


FORM-IN-PLACE SEALS FOR WEATHERPROOF!NG 20-10-1009Maintenance Practices 201

AERODYNAMIC SMOOTHING SEALANT 20-10-3003Maintenance Practices 201

HIGH TEMPERATURE SEALANTS (SILCOSET AND SILASTIC) 20-10-3005Maintenance Practices 201

METAL FILLED EPOXIES FOR GAP FILLING 20-10-3008Maintenance Practices 201


RayNteon Aircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME



APPLICATION OF COLD CURING EPOXY PRIMER

TO INTERNAL AND EXTERNAL SURFACES 20-10-3527


APPLICATION OF FLEXIBLE AND PERMEABLE FINISHTO AIRPLANE INTERNAL SURFACES 20-10-3528


APPLICATION OF POLYURETHANE FINISHING ENAMEL FOR THEOVERCOATING OF SEALANTS 20-10-3534

Maintenance Practice 201

APPLICATION OF ANTISTATIC PAINT TO COMPOSITE MATERIALS

OTHER THAN CARBON FIBER 20-10-3537


BONDING SILICONE RUBBERS 20-10-4005Maintenance Practice 201

BONDING RUBBER AND P.T.F.E. TO PERSPEX OR METAL 20-10-4007


BONDING WITH EPOXY ADHESIVES FOR NON STRUCTURAL PARTS 20-10-4011Maintenance Practices 201

RUBBER BONDING ADHESIVE 20-10-4012


BONDING WITH CONTACT ADHESIVE 20-10-4014Maintenance Practices 201

BONDING WITH SCOTCH-SEAL METAL SEALANT 2084 20-10-4016


SHRINK FITTING OF BOLTS, BUSHES, PINS, ETC. 20-10-4501Maintenance Practices 201

LOCKING OF THREADS WITH ANAEROBIC ADHESIVE 20-10-4507Maintenance Practices 201

RETENTION OF BUSHES AND BEARINGS BY LIQUID SEALANT 20-10-4553Maintenance Practices 201

ELECTRICAL BONDING 20-10-5016Maintenance Practices 201

DEGREASING OF METALLIC MATERIALS 20-10-9053Maintenance Practices 201


Rayfheoll Aircraff Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME



PREPERATION OF RUBBER SURFACES FOR BONDING 20-10-9070


VERY HIGH TEMPERATURE SEALANTS 20-11-1040


I PRECIPITATION STATIC (P-STATIC) TEST 20-11-1041Maintenance Practices 201STORES DATA

NOTE: For information concerning servicing, storage, shelf life, transportation etc. of vendorcomponents, refer to the relevant vendor publication.

CONSUMABLE MATERIALS

CONSUMABLE MATERIALS 20-95-00

Approved Suppliers 1

CONSUMABLE MATERIALS 20-95-11Greases and Lubricants 1

CONSUMABLE MATERIALS 20-95-101Fluids and Oils 1


Cleaning Agents, Paint Strippers and Release Agents 1


Adhesives, Jointing and Sealing Compounds 1


Enamels, Lacquers, Paints, Primers and Varnishes 1

CONSUMABLE MATERIALS 20-95-501Chemical and Electro/Chemical Surface Finishes 1

CONSUMABLE MATERIALS 20-95-601Miscellaneous Materials 1

20-CONTENTSPage 4Jun.OS

Rayiheon Aircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

LIST OF EFFECTIVE PAGES INTRODUCTION

CH-SE-SU PAGE DATE

Introduction 1 thru 5 Mar.OG

INTRODUCTION-LOEPPage 1 of 1

Mar.OG


INTRODUCTION

i. INFORMATION

NOTE: Throughout this Standard Practices Manual where Hawker 800XP is referenced, the designation ofHawker 850XP equally applies.

All commercial publications are listed on the web at http:llpubs.raytheonaircraft.com. For more information onthese publications, contact the Technical Manual Distribution Center (TMDC) at 1-800-796-2665 or (316)676-8238, fax (316) 671-2540, or E-mail [email protected] reissues or revisions are automatically provided to the holder of this manual. For information on howto obtain reissues or revisions applicable to this manual, refer to the latest revision of the Raytheon AircraftCompany Service Bulletin No. 00-2001 or visit our web site at http:llpubs.raytheonaircraft.com., then selectSubscription Services Information.

Additional publications are listed in the current Electronic Directory of Catalogs and Services (EDOCS)CD-ROM (P/N 994-32808). For Information on these publications contact the Technical Manual DistributionCenter (TMDC) at 1-800-796-2665 or (316) 676-8238, fax (316) 671-2540, E-mail [email protected] orvisit our web site at http://pubs.raytheonaircraft.com., then select Searchable Publications Status and PriceList.

Additional publications are listed in the current Publications Price List (P/N 118556). Contact your nearestRaytheon Aircraft Service Center for information on these publications or visit the Publications price list website at http://pubs.raytheonaircraft.com.The Raytheon Electronic Publication System (REPS) contains selected Manuals in a digital format. Thismanual, along with others, is available on CD-ROM. Optional paper copies of the manuals on the CD-ROMare available for purchase.

A. General

The 125/Hawker All Series Chapter 20 Standard Practices manual is prepared in accordance with therequirements of ATA (Airline Transport Association of America) Specification 2200 with respect to thearrangements and content of the Chapter/System with the designated numbering system. The manualhas one volume and covers all series 1251Hawker airplanes.

This manual describes the physical and chemical processes which require the use of chemicals,solvents, paints, and other commercially available materials. The user of this manual should obtain theMaterial Safety Data Sheets (MSDS) from the manufacturers or suppliers of the materials to be used.The user must be completely familiar with the manufacturer/supplier information and obey theprocedures, recommendations, warnings and cautions set forth for the safe use, handling, storage anddisposal of the materials.

Updated specification numbers and material equivalents or acceptable alternatives have been approvedby the Raytheon Aircraft Process and Environmental Laboratory (Dept. 037, nonmetallic section)Wichita, Kansas, USA.

Manufacturers, where known, are listed in the Suppliers Code column and correspond to section20-95-00 where current manufacturer names and addresses are provided.It shall be the responsibility of the owner/operator to ensure that the latest revision of the publicationsreferenced in this manual are utilized during operation, servicing and maintenance of the airplane.

INTRODUCTION PMaaSreg~

Rayfheon Aircraft Company1~MHAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

Raytheon Aircraft Company expressly reserves the right to supersede, cancel and/or declare obsoleteany parts, part numbers, kits or publications that may be referenced in this manual without prior notice.

WARNING: Use only parts obtained from sources approved by Raytheon Aircraft Company, inconnection with the maintenance and repair of Raytheon Aircraft Companyairplanes.

WARNING: Genuine Raytheon Aircraft Company parts are produced and inspected underrigorous procedures to insure airworthiness and suitability for use in RaytheonAircraft Company airplane applications. Parts purchased from sources other thanthose approved by Raytheon Aircraft Company, even though outwardly identical inappearance, may not have the required tests and inspections performed, may bedifferent in fabrication techniques and materials, and may be dangerous wheninstalled in an airplane.

WARNING: Salvaged airplane parts, reworked parts obtained from sources not approved by theRaytheon Aircraft Company or parts, components or structural assemblies, theservice history of which is unknown or cannot be authenticated, may have beensubjected to unacceptable stresses or temperatures or have other hidden damage,not discernible through routine visual or usual nondestructive testing techniques.This may render the part, component or structural assembly, even though originallymanufactured by the Raytheon Aircraft Company, unsuitable and unsafe for airplaneuse.

WARNING: Raytheon Aircraft Company expressly disclaims any responsibility for malfunctions,failures, damage or injury caused by use of parts not approved by the RaytheonAircraft Company.

B. Correspondence

If a question should arise concerning the care of your airplane, it is important to include the airplaneserial number in any correspondence. The serial number appears on the model designation placard.Refer to Chapter 11 of the Illustrated Parts Catalog for Placard location.

C. Publications Change Request (PCR)If an irregularity or missing information is noted, the user of this manual may access a PCR form at http://www.pubs.raytheonaircraft.com., select Forms and Reports and then select Publication ChangeRequest. This form and the information that was entered will be electronically forwarded to RaytheonAircraft Customer Support. The change request will be researched for any necessary updates to thepublication. Assistance is available, at any time, by contacting Raytheon Aircraft Technical Support at800-429-5372 or 316-676-3140.

D. Normal Revisions

Normal Revisions to this manual are issued to provide changes to standard practices information.

i. Paper Revision

That portion of text which has been revised by the addition of, or a change in, information isdenoted by a solid revision bar adjacent to the text. Each revised page will ONLY showrevision bars for text changed by the revision. There will not be a revision bar if text wasdeleted from the page.

Revised illustrations will be identified by a revision bar printed on the side of the page.

Mar.OGINTRODUCTION


2. CD-ROM Revision

Normal revised text on the CD-ROM will be highlighted yellow across the revised passage oftext. For each revision of this manual, a new CD-ROM will be issued.

The CD-ROM may contain revised illustrations. Revisions to the illustrations are notidentified

E. Temporary Revisions

Temporary Revisions to this manual are issued to provide standard practices information in the interimbetween normal revisions. Each temporary revision is issued by the chapter number to which it applies,followed by a sequential number in the order of publication (Temporary Revisions 20-1, 20-2, etc.). Ifrelevant, the information in the temporary revision should be included in the next normal revision of themanual.

i. Paper Temporary Revisions

Temporary Revisions are printed on yellow paper and are to be inserted in the maintenancemanual in accordance with the instructions provided and adjacent to applicable chapter,section, and subject matter in the manual.

2. CD-ROM Temporary Revisions

A new CD-ROM will be issued for each Temporary Revision to this manual. This informationis listed in conjunction with the applicable chapter, section, subject on the CD-ROM.

F. Revised Text

That portion of text which has been revised by the addition of, or a change in, punctuation and/orinformation is denoted by a solid revision bar adjacent to the textual column in the margin of thisparagraph. Each page may or may not have revision bars. That date printed on the bottom of each pageindicates when the information on that page was changed. Each page will ONLY show revision bars forpunctuation and/or text changed by the current revision. Revised text in REPS will be denoted by yellowhighlighting.

G. Revised Illustrations

When an illustration is modified or a new illustration is added, it will be noted by a solid line (revision bar)along the outside margin of the illustration.

H. Warnings, Cautions and Notes

WARNING Brings attention to an operating procedure, inspection or maintenance practice,which if not correctly followed, could result in personal injury or loss of life.CAUTION Brings attention to an operating procedure, inspection, repair or maintenancecondition, which if not strictly observed, could result in damage or destruction of equipment.

NOTE Brings attention to an operating procedure, inspection, repair or maintenancecondition, which is essential to highlight.

INTRODUCTION

Raylheon AiKraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

2. MANUAL LAYOUT

A. Title Page

A Title page is located at the beginning of the manual and provides the part number of the manual, andlists all aircraft models pertaining to this manual. Information throughout this manual is applicable to allmodels listed on the title page except where specifically stated.

B. Record of Revisions (Normal) PageThe printed manual will have a Record of Revisions page. The Record of Revisions is provided followingthe Title page. When a revision is inserted, the revision number, the date the revision is inserted into themanual, and the initials of the person(s) inserting the revision should be recorded on this page.

C. Record of Temporary Revisions Page

The printed manual will have a Record of Temporary Revisions page. The Record of TemporaryRevisions Page is located following the Record of Revisions page. When a temporary revision isinserted or removed from this manual, the appropriate information should be recorded on this page.

D. Introduction- LOEP

The introduction has a separate List of Effective Pages and lists the issue date of each page.

E. Introduction

The introduction follows the Introduction LOEP

F. Chapter 20 LOEP

The printed manual has a Chapter 20 List of Effective Pages. The List of Effective Pages follows theIntroduction and lists the issue date of each page that is effective for that chapter.

G. Chapter 20 Table of Contents Pages

The printed manual has a Chapter 20 Table of Contents Pages. The Chapter Table of Contents Pagesfollow the Chapter 20 List of Effective Pages and lists the contents of the data for that chapter.

H. Existinglprevious ATA numbers table

This table gives a cross reference where a topic, which previously existed in an AMM may still bereferred to. Where topics have been replaced by more up to date procedures the latest procedure canbe found by cross checking the old AMM reference against the new reference in this manual.

3. HOW TO USE THE MANUAL

A. ATA Subject Matter AssignmentThe contents of this manual are organized into three levels. The three levels are:

(1) Level~- ChapterlSystem

INTRODUCTION

Aircraft tompany125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

The various procedures are broken down into two major groups, Standard Practices andConsumable Materials. They are assigned a number, which becomes the first element of thestandardized numbering system. Thus the element "20" of the number 20-95-11 refers to theChapter "STANDARD PRACTICES".

(2) Level 2-Subsystem/SectionThe chapterlsystem of a procedure is broken down into subsystems/sections. These subsystemsare identified by the second element of the standard numbering system. The element "95" of thenumber 20-95-11 concerns itself with Consumable Materials.

(3) Level 3-Unit/SubjectThe individual units within a subsystemlsection may be identified by the third element of thestandard numbering system. The element "11" is a subject designator. This element is assigned atthe option of the manufacturer and may or may not be used. In this example, the subject is"Greases and Lubricants".

(4) Additional Data Page Block

The data may be additionally broken down into page blocks.

(a) Page Block 0 Page 1 thru 99 System Description

(b) Page Block 2 Page 201 thru 299 Maintenance Practices

B, References to Procedures, Figures, Equipment and Materials

A system has been developed to provide a method of allowing the user to quickly locate data referred toin the other manuals. This system provides information for both the printed manual as well as ahyperlink in electronic manuals.

Here are a few examples:When the user is directed to information in another manual, the text will be as follows: Refer toFASTENERS IDENTIFrCATrON (Ref. 800-SRM, 51-41-00, 001). The information is found in Chapter51-41-00 within page block 001 of the Structure Repair Manual.

When the user is in a procedure and is directed to information about a tool or piece of equipment, forexample an Axle Jack, the text will be as follows: (Ref. 1TEM-125-111000, 07-10-26). The Axle Jackinformation is found in Chapter 07-10-26 of the Illustrated Tool and Equipment Manual.

INTRODUCTION PMaaSreg~

Existing/previous ATA numbersI m~G: =I~DX(T) m

This table gives a cross reference where a topic, which previously existed in an AMM may still be referred to. Where topics have been replaced byoq I more up to date procedures the latest procedure can be found by cross checking the old AMM reference against the new reference in this manual.88 SERIESoo

SERIES 800, 800XP SERIES0" 125/H-20 Chapter title 125/H-20 1-700 800XP 1000PRO LINE 21

GENERAL 20-00-00 N/A N/A N/A

TORQUE LOADING 20-09-20 20-09-20 20-09-20 20-09-01 1RETENTION OF BEARINGS BY W AND S RETAINING RINGS 20-09-21 20-09-21 20-09-21 20-09-21 n

o 231REUSE OF SELF-LOCKING NUTS 20-09-23 20-09-23 20-09-23 20-09-23 I CPCOMPONENT LOCKING 20-09-41 N/A N/A N/A g

FLARING OF STAINLESS STEEL TUBES 20-09-91 20-09-91 20-09-91 20-09-91

COUNTERSUNK HEAD BOLTS 20-09-141 20-09-141 20-09-141 20-09-04z ~13APPLICATION OF ALOCROM 1200 (ALODINE 1200) 20-10-08 20-10-04 20-1 0-08 20-10-11CONTROL CABLES (EXAMINATION AND REJECTION CRITERIA) 20-10-31 20-10-31 20-10-31 20-10-31CONTROL CABLE (CORROSION PROTECTION) 20-10-32 20-10-32 20-10-32 20-10-32 PrSTRIPPING OF PAINT 20-10-33 20-10-33 20-10-33 20-10-10 -1

20-1 0-822 ~nv, O

CHEMICAL REMOVAL OF POLYSULPHIDE (PRC) SEALANTS 20-1 0-34 N/A N/A N/A jn 1P3h) I VACU-BLASTING WITH DRY ALUMINA GRIT 20-1 0-40 N/A 20-1 0-40 20-1 0-40 -n PrO WIRING PROCEDURES AND REPAIR 20-10-50 N/A N/A NIA

APPLICATION OF SODIUM ALGINATE RELEASE AGENT 20-10-75 20-10-75 20-10-75 20-10-21 CC~b APPLICATION OF URETHANE FINISH TO EXTERNAL SURFACES 20-1 0-228 N/A N/A N/A

LEAK TESTING FLUID (NEODOL 91-6) 20-1 0-354 20-1 0-354 20-1 0-354 20-10-22LEAK TESTING FLUID (SHERLOCK) 20-10-355 Topic deleted now covered by 20-10-354.SEALING COMPOUND FLEXIBLE SEAL APPLICATIONS 20-10-447 20-10-447 20-10-447 20-10-23

~L clnELECTRICALLY CONDUCTING JOINTING COMPOUNDS 20-10-481 20-10-481 N/A N/A

I m

=I I I I I SERIESa SERIES 800, 800XP SERIES125/H-20 Chapter title 125/H-20

-1 1-700 800XP 1000~n PRO LINE 21

8 8 THE APPLICATION OF ACID RESISTING PAINT 20-10-482 20-10-482 20-10-482 20-10-24oo

SEALING OF PERSPEX AND LAMINATED GLASS WINDOWS AND 20-10-499 20-10-499 N/A N/Ao PANELS

o

gRENOVATION OF FURNISHING MATERIALS 20-10-560 20-10-560 20-10-560 20-10-25POLISH AIRCRAFT SKINS (EXTERNAL) 20-10-811 20-10-811 N/A N/A iSEALING OF INTEGRAL FUEL TANKS WITH POLYSULFIDE TYPE 20-10-1001 20-10-1001 20-10-1001 20-10-03 xCOMPOUNDS n

SEALING OF PRESSURE CABINS AND AREAS OUTSIDE INTE- 20-1 0-1 002 20-1 0-1 002 20-1 0-1 002 20-10-04 gGRAL FUEL TANKS WITH POLYSULFIDE TYPE COMPOUNDS qFORM-IN-PLACE SEALS FOR WEATHERPROOFING 20-10-1009 N/A N/A N/A n

AERODYNAMIC SMOOTHING SEALANT 20-10-3003 20-10-3003 N/A NIA o,

HIGH TEMPERATURE SEALANTS SILCOSET AND SILASTIC 20-10-3005 20-10-3005 N/A NIA zg J

METAL FILLED EPOXIES FOR GAP FILLING 20-10-3008 20-10-3008 20-10-3008 N/A n h

APPLICATION OF COLD CURING EPOXY PRIMER TO INTERNAL 20-10-3527 20-10-453 N/A N/A ~D PIAND EXTERNAL SU RFACES 20-10-500

20-1 0-3512 7o n

20-23-0 oAPPLICATION OF FLEXIBLE AND PERMEABLE FINISH TO 20-10-3528 20-1 0-500 20-1 0-42 20-1 0-12 3AIRPLANE INTERNAL SURFACES 20-10-3504 20-10-3504 20-10-29

hi 20-21-0 20-21-0 20-1 0-3020-22-0 20-22-0

YAPPLICATION OF POLYURETHANE FINISHING ENAMEL FOR THE 20-10-3534 NIA NIA NIAb OVERCOATING OF SEALANTS.APPLICATION OF ANTISTATIC PAINT TO COMPOSITE MATERIALS 20-10-3537 20-11-1019 20-11-1019 20-10-09OTHER THAN CARBON FIBER

BONDING SILICONE RUBBERS 20-10-4005 20-10-4005 20-10-4005 20-10-27

rn BONDING RUBBER AND PTFE. TO PERSPEX OR METAL 20-10-4007 20-10-4007 20-10-4007 20-10-28

i m

=I I I I I SERIESm SERIES 800, 800XP SERIES

125/H-20 Chapter title 125/H-20 1-700 800XP 1000v, PRO LINE 21

oBONDING WITH EPOXY ADHESIVES FOR NON STRUCTURAL 20-1 0-4011 N/A 20-1 0-4011 20-1 0-17PARTS

o RUBBER BONDING ADHESIVE 20-10-4012 20-10-4012 20-10-4012 N/An I BONDING WITH CONTACT ADHESIVE 1 20-10-4014 1 20-10-312 1 20-10-31~ 1 N/A I F;

BONDING WITH SCOTCH-SEAL METAL SEALANT 2084 1 20-10-4016 N/A N/A N/A ZUrSHRINK FITTING OF BOLTS, BUSHES, PINS, ETC. 20-10-4501 20-10-4501 20-10-4501 20-10-4501

nLOCKING OF THREADS WITH ANAEROBIC ADHESIVE 20-10-4507 20-10-4507 N/A N/A

RETENTION OF BUSHES AND BEARINGS BY LIQUID SEALANT 20-10-4553 N/A N/A N/A CPELECTRICAL BONDING 20-10-5016 20-10-5016 20-1 0-5016 20-10-01

DEGREASING OF METALLIC MATERIALS 20-10-9053 N/A N/A N/A

PREPARATION OF RUBBER SURFACES FOR BONDING 20-10-9070 N/A N/A N/A

VERY HIGH TEMPERATURE SEALANTS 20-11-1040 20-11-1040 20-11-1040 20-10-08 1 g~i

PRECIPITATION STATIC (P-STATIC) TEST 20-11-1041 N/A N/A N/A o i4CONSUMABLE MATERIALS APPROVED SUPPLIERS 20-95-00 20-95-00 20-95-00 20-95-00

CONSUMABLE MATERIALS 20-95-11 20-95-11 20-95-11 20-95-11 nGrease and lubricants I I I I I ii; OCONSUMABLE MATERIALS 20-95-101 20-95-101 20-95-101 20-95-101

I Fluidsand oils I I I I I XCONSUMABLE MATERIALS 20-95-201 20-95-201 20-95-201 20-95-201 3Cleaning agents, paint strippers and release agents CC:CONSUMABLE MATERIALS 20-95-301 20-95-301 20-95-301 20-95-301

Adhesives, jointing and sealing compoundsCONSUMABLE MATERIALS 20-95-401 20-95-401 20-95-401 20-95-401

CONSUMABLE MATERIALS 20-95-501 20-95-501 20-95-501 20-95-501

Enamels, lacquers, paints, primers and varnishes

sm Chemical and electro/chemical surface finishes

I m

9 2: =I I I I I SERIESSERIES 800, 800XP 8 SERIES

1 7 125/H-20 Chapter title 125/H-20 1-700 800XP 1000PRO LINE 21O

8 8 CONSUMABLE MATERIALS 20-95-601 20-95-601 20-95-601 20-95-601oo

Miscellaneous

8BC)

v, Oi3TI Iph> B n,

O

;I

U1,

CHAPTER

STANDARDPRACTICES(AIRFRAME)

Raytheon AircraftI25/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

GENERAL- DESCRIPTION

WARNING: WHEN YOU USE ANY OF THE MATERIALS LISTED IN THIS MANUAL, OBEY ALLWARNINGS AND CAUTIONS FOR USE, HANDLING, STORAGE AND DISPOSAL ASRECOMMENDED ON THE MANUFACTURERS OR SUPPLIERS DATA SHEETS.

CAUTION: IDENTIFY WITH A CODE, FLIGHT CONTROL CABLES, PIPES, ELECTRICAL CONNECTORSOR WIRES DISCONNECTED DURING MAINTENANCE. THIS WILL HELP YOU INSTALL

THEM CORRECTLY AGAIN. AFTER CONNECTION REMOVE ALL IDENTIFICATION CODES.

MAK~ SURE THE SYSTEM WORKED ON AND THE ASSOCIATED SYSTEMS FUNCTIONCORRECTLY BEFORE YOU RETURN THE AIRPLANE TO SERVICE.

1. General

This manual describes physical and chemical procedures which require the use of commercially availablematerials. Descriptions, maintenance practices and inspections for Hawker Airplanes are included.

These processes are based upon current and accepted specifications. The consumable materials havebeen reviewed and approved for use by the Raytheon Aircraft Process and Environmental Laboratory.

International material equivalents and/or alternate products are included where possible. Helpfulinformation has been added to the remarks column.

EFFECTIVITY: 20-00-00125 Series 1-1000 Page 1Hawker 800, 1000, 800XP Jun.02


STANDARD PRACTICES -AIRFRAME

TORQUE LOADINGMAINTENANCE PRACTICES

INFORMATION I

EquipmentlMaterials Partlltem No.Grease 034 (Chapter 20-95-11)Mineral oil 126 (C hapter 20-95-1 01Engine oil 137 (Chapter 20-95-101)Cleaner, solvent 201 (Chapter 20-95-201) 1Methylated spirits 227 (Chapter 20-95-201) 1Paint, black 440 (Chapter 20-95-401) 1Lint free cloth 621 (Chapter 20-95-601) 1Wire, corrosion resistant 651 (Chapter 20-95-601) 1Brush 676 (Chapter 20-95-601) 1Torque Equipment Local supply I

Nuts which are torque loaded use locking devices which are incorporated in either the nuts or the necessarywashers. Torque loading is applied to nuts and bolts (including setscrews) to prevent critical overstressingwith the possibility of subsequent failure of the part. The torque figure quoted for each application also givesmaximum security and even tightening.

Engine oil (Item 137) or light mineral oil (i2em 128) is used as a lubricant on threads of nuts and bolts, exceptwhere prelubricated nuts are used.

Mandatory and non-mandatory torque loadings are specified in the maintenance instructions. Do not exceedthe maximum torque limit to align a lock pin or tab washer. If a locking position can not be aligned within thespecified torque limits, either change the nut, loosen the nut and tighten to 90% of the specified minimumtorque, or add a washer.

2. USE OF EXTENSION SPANNERS

To obtain the correct reading, the handle of the torque wrench must be held with one hand only, the thumbgripping the handle, not lying along it. The extension spanner should be in line with the center of the torquewrench. VVhen a horizontal extension spanner or extension piece is used in with a torque wrench, the actualload applied when torque tightening will be of a greater value than that set on the torque wrench. To calculatethe torque setting for a required torque loading use the following formula:

WRequired torque setting actual torque setting x W+E

W distance between center of torque head and center of wrench handle.E length of extension spanner between centers.

20-09-20

RBIYCheOn Aircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

A. Example, Ibf in.

To find the torque setting for a specified load of 75 Ibf in. when using a 3 inch extension spanner and a10

12 inch long wrench (10 inches between centers): 75 x 581bf in.10+3If the torque wrench being used does not incorporate a scale or dial, e.g. the breaking type, theextension must be interposed between the wrench and the setting rig during the setting procedure.

B. Example,Nm

To find the torque setting for a specified load of 8.0 Nm when using a 75 mm extension and a torque300

wrench with an effective length of 300 mm: 8 x 6.4Nm300 75

If the torque wrench being used does not incorporate a scale or dial, e.g, the breaking type, theextension must be interposed between the wrench and the setting rig during the setting procedure.NOTE: A setting rig must be used to set a break back, or other torque wrench without a scale or dial.

V EXTENSION SPANNERTORQUE WRENCH

M1605 O

Figure 201Correct Method of Holding a Torque Wrench

Jun.04~of" 20-09-20


3. PIPE CONNECTORS

A. AN Pipe Connectors

NOTE: The following information on AN Connectors applies only to airplanes with Honeywell enginesand to series 1000 airplanes.

(1) Torque tighten AN pipe couplings to between the minimum and maximum torque (Ref. Table 201)or (Ref. Table 202) as appropriate. AN adapters in manifolds are to be tightened to between thelimits (Ref. Table 203).

(2) Only use the tightening torques in (Table 201) if both parts of the connection are steel. Thisincludes the assembly of steel end fittings on flexible pipes to steel connectors.

(3) If one or both parts of a connection is of light alloy, use (~Table 202). This applies to light alloy pipeor hose end fittings assembled to steel connectors.

(4) Tightening to the appropriate value in (Table 201), (Table 202) or (Table 203) gives adequatemechanical resistance to prevent the connection being loosened by vibration.

(5) To make sure that the pipe flare and union take up set when assembling a connection with a newpipe or union:

(a) Tighten to a torque 10% higher than the value specified.

(b) Loosen the nut two turns.

(c) Tighten to the specified value.

(d) Paint a line across the joint using a brush (Item 676) and black paint (Item 440).B. AGS Pipe Connectors

(1) Torque tighten all steel to steel pipe to pipe and pipe to component connectors in accordance with(Table 201). This includes all flexible hoses with steel end fittings.

(2) Torque tighten all light alloy to light alloy pipe to pipe and pipe to component connectors inaccordance with (Table 202). This includes all flexible hoses with aluminum end fittings.

(3) Torque tighten all steel or light alloy adapters into manifold blocks in accordance with (Table 203).

(4) To minimize the risk of leakage at joints do as follows:

(a) Tighten the nut to a torque approximately 10% higher than the value specified.

(b) Loosen the nut two turns.

(c) Torque tighten the nut to the specified value.

(d) Lockwire(ltem 65l)the coupling as required.

20-09-20

RayMheon Aircraft Company125/HAVVKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

Table 201Torque Tightening of Steel AN and AGS Pipe Couplings

AN connection AGSconnection Torque Ibf in. Torque Nmsize size Min. Max. Min. Max.

-3 3116 95 105 10.73 11.29

-4 1/4 135 150 15.25 16.29

-5 5/16 170 200 19.21 22.60

-6 3/8 270 300 30.51 33.89

-8 1/2 450 500 50.84 56.49

-10 518 650 700 73.44 79.09

-12 3/4 900 1000 101.68 112.98

Table 202

Torque Tightening of Light Alloy AN and AGS Pipe Couplings

AN connection AGSconnection Torque Ibf in. Torque Nmsize sire Min. Max. Min. Max.

-3 3/16 25 35 2.82 3.95

-4 1/4 50 65 5.65 7.34

-5 5/16 70 90 7.91 10.17

-6 3/8 110 130 12.43 14.69

-8 112 230 260 25.99 29.38

-10 5/8 330 360 37.28 40.67

-12 3/4 460 500 51.97 56.49

Table 203

Torque Tightening of Steel and Light Alloy AN and AGS Adapters into Manifold Blocks

AN connection AGSconnection Torque Ibf in. Torque Nmsize size Min. Max. Min. Max.

-3 3/16 65 75 7.34 8.47

-4 1/4 95 105 10.73 11.86

-5 5/16 120 130 13.56 14.69

-6 3/8 155 165 17.51 18.64

-8 1/2 280 305 31.64 34.46

-10 5/8 380 405 42.93 45.76

-12 3/4 550 600 62.14 67.79

20-09-20

RBylheon Aircraft Company125lHAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

4. MANDATORY TORQUE LOADING IDENTIFICATION

Normally removable bolts and nuts which must be torque loaded on assembly are identified as follows:

Bolt heads and nuts are painted black (Item 440) and a black letterT 1/8 to 3116 in. (3 to 4 mm)high is painted, on the adjacent structure.Holes are marked with a black painted (Item 440) ring which contains a black letterT 1/8 to 3116in. (3 to 4 mm) high.Groups of bolts or nuts are contained within one black painted (Item 440) ring, with a black letterT1/8 to 3/16 in. (3 to 4 mm) high marked close to the center of the group.All markings must be readily Visible with normal vision.

NOTE: Before mid-1977 the manufacturers procedure of identifying normally removable nuts and bolts whichrequire to be torque loaded on assembly was as follows:

Bolt-heads and nuts were painted red after final assembly in the structure.

A red ring was painted around the bolt hole on the structure together with a red letterT.

5. NON-MANDATORY TORQUE LOADINGS

For nut and/or bolts, which are not detailed as being subject to a mandatory torque loading, the followingvalues are given for guidance:

Table 204Guidelines for Non-mandatory Torque Loadings

Torque Loading Ibf in. (Nm)Thread Size High Strength Steel Normal Steel Light Alloy

75 Ton x 2240 168,000 Ibs 55 Ton x 2240 =123,200 Ibs I I I3/16in./No.10 30-35(3.39-3.95) 20-25(2.26-2.82) 10-15(1.13-1.69)

114 in. 60 70 (6.78 7.91) 45 50 (5.08 5.65) 25-30(2.82 3.39)5/16 in. 115

-125(12.99 14.12) 85 90 (9.60 -10.17) 45 50 (5.08 5.65)3/8 in. 195 230 (22.03 25.99) 145 170 (16.38 19.21) 75 90 (8.47 10.17)

7/16 in. 290 335 (32.77 37.85) 215 250 (24.29 28.25) 115 130 (12.99 -14.69)1/2 in. 425 490 (48.02 55.37) 315 365 (35.59 41.24) 170 195 (19.21 22.03)

9/16 in. 600 690 (67.80 77.97) 450 515 (50.85 58.19) 240 275 (24.12 31.07)5/8 in. 760 890 (85.88 100.56) 570 665 (64.41 75.14) 300 355 (33.90 40.11)

For bolt specifications and materials refer to the Structural Repair Manual (SRM) 51-41-00.For 160 168 KSI bolts use the torque values in column 1 (High Strength Steel).For 123 KSI bolts use the torque values in column 2 (Normal Steel).For 64 KSI bolts use the torque values in column 3 (Light Alloy).

20-09-20

RB~heOn Aircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

6. ~-CLAMPS

To make sure that friction or slight misalignment does not prevent V-clamps from being properly tightened, themating faces of the clamp and the coupling flanges are to be lubricated. Unless otherwise stated, use grease(Item 034).

7. TORQUE TIGHTENING OF TENSION FASTENERS IN JOINTS WITH POLYSULFIDEINTERFAY

Polysulfide sealant can exude from joints contained by fasteners during the curing period of the sealant,causing a loss of pre-tension. This is unacceptable in the case of tension fasteners which are torqued to apre-determined level. To overcome this loss of pre-tension it is necessary to tighten tension fastenersprogressively during initial curing of the assembly before final locking. Methods 1 and 2 are given to coverfasteners and nuts assembled without and with grease. Where no method is specified by the manufacturerMethod 1 is to be used.

A. Assembly Without Grease (Method(1) Clean the fastener threads, unlubricated nuts and the faces (i.e. structure face, washer face and

the nut or fastener seating face) at the end where the torque spanner is applied. Clean the itemand face with a clean lint free cloth (Item 621) dampened with solvent (Item 201) or (Item 227)then wipe dry with a clean dry cloth before solvent is dry.

(2) Make sure the fastener, nut threads and seatings are clean and that there is no condensationpresent, due to the cooling effect (through evaporation) of the cleaning solvent.

NOTE: Lubricants on self- lubricated nuts are not to be removed unless expressly authorized bythe manufacturer. The torque settings quoted by the manufacturer take account of the nutconditions (i.e. self lubricated or lubricant removed).

(3) Tighten fasteners in sequence to the required torque value and note the sequence for subsequenttightening.

(4) Wait a minimum of 2 hours and repeat paragraph 7.A. (3).

(5) Repeat 7.A. (3) and (4) until a stable condition exists and no further movement is observed.Complete this within the initial cure time of the sealant being used.

(6) Lockwire or split pin the nut as required.NOTE: Double wire locking is preferred and is essential if the locking wire is long and is

unsupported and/or can become damaged. Single wire locking is permissible if the lockinglength is short and lays close to the component locked.

B. Assembly with Grease (Method 2)(1) Clean the fastener threads with a clean lint free cloth (Item 6321) dampened with solvent (Itc?m 201)

or (Item 227) then wipe dry with a clean dry cloth before the solvent is dry.

(2) Apply grease to the threads and mating surfaces in accordance with the manufacturersrequirements.

(3) Do operations in paragraph 7.A. (3) to (6)

20-09-20

Raytheon Aircraft Company12S/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

8. INSPECTION

A. Procedure

(1) Make sure that the correct torque equipment, set to the correct torque setting, is used throughoutand is correctly calibrated.

(2) Make sure that the fasteners are tightened in the correct sequence and that there is no relativemovement between the nut and fastener when the specified torque is applied.

(3) Make sure that lockwire/split pins are to an acceptable standard.

(4) Make sure that all inspection procedures are carried out within the cure time of the sealant.

20-09-20 Page 207Jun.04

Raytheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

RETENTION OF BEARINGS BY W AND S RETAINING RINGSMAINTENANCE PRACTICES

i. General(Figure201)A Walker and Schofield (W and S) bearing retaining ring, capable of sustaining an incidental side load ofup to 100 Ib., consists of a light alloy ring which is pressed into a housing groove with special tools. Thisring is a truncated cone in shape before insertion, and, when fitted, forms a fiat retainer, similar to awasher. In combination with its mating ring or an abutment in the housing, the W and S ring will rigidlyclamp in either ball, self-aligning or roller bearings.

Each groove is spaced to suit a standard ring or rings in the bearing housing and approved tools onlymust be used for cutting the groove or grooves. As shown, bearings can be held by a retaining ring oneach side or by means of an abutment in the housing and one retaining ring. When strength considerationspermit, a 3/32 in. diameter, axial extraction groove is also cut into the housing. This enables the visibleportion of the ring to be drifted radially inward, distorting it sufficiently clear of the retaining groove at thispoint and enabling it to be gripped by pliers and pulled out.

Due to variations in the size of corner radii on the outer races of standard bearings, complete clamping ofthe bearing may not be achieved when using standard rings. It is imperative therefore to make sure thebearing is not axially slack after insertion of rings. When any slackness is found, the assembly concernedmust be rejected and one or both of the standard rings must be removed and replaced by an Overthickring or rings.

When replacing a bearing during the course of a normal overhaul or during field service, it may benecessary to fit an Overthick ring or rings in order to clamp the new bearing properly, due to the radii onthe corners of the new bearing not being the same as those on the old bearing. It is also possible that abearing originally fitted with standard rings may be found to have worked loose in service. In such casesan Overthick ring or rings should be fitted, in place of the existing ring or rings, so that the bearing isproperly clamped.

Overthick rings are the next even standard wire gage (s.w.g.) thicker, are finished in anodic yellow andhave the suffix O after their normal part number; thus, a plain finish 22 s.w.g. A18Y ring will be thestandard ring, and a yellow finish 20 s.w.g. A18YO ring will be the Overthick one.

W and S retaining rings with suffix letter X may be encountered in service. to enable existing stocks ofthese rings to be used up they should be fully annealed before use and left in this condition. Rings withsuffix letter Y are in current use and may be used as supplied. Instructions for removal and insertion ofeach type of ring are identical.

Because of a certain amount of spring-back which occurs when the ring is pressed into its groove, it is notexpected to lie completely flush with the outer face of the bearing; therefore, do not resort to excessivepressing operations in an attempt to make the ring lie flush.

Inspection must check that housing lips are free from cracks after the rings are fitted. It must also be madesure that the rings have entered the grooves without deformation; thickening of the rings, either generallyor locally, usually denotes excessive resistance to insertion and is not acceptable.

NOTE: BEARINGS RETAINED BY SPUN-IN BUSHES REMOVAUINSTALLA TION (20-09- 101~ maybe found in the Hawker 800 and 800XP, BAe 125 Series 800A and 8008 Overhaul Manual(OM 125-800).

EFFECTIVITY: 20109-21125 Series 1-1000 Page 201Hawker 800, 1000, 800XP Jan. 2001


RINGBEFORE III 1 II II I II RING PRESSEDUSE I II II I II FLAT

WALKER 8 SCHOFIELD 01y 8 S)RETAINING RING

RETAINING RING RETAINING RINGGROOVES GROOVE

SELF ALIGNING BEARINGBEARING HOUSING

GROOVE

SELF-ALIGNING SHPERICALBEARING RETAINED BY AW& S RING AT EACH SIDE SELF-ALIGNING SPHERICAL

BEARING RETAINED BY ANABUTMENT AND ONE W 8 S RING

AXIAL GROOVEFOR EXTRACTION

OBALL BEARING BEARING

HOUSING

BALL BEARING RETAINEDBY A W& S RING AT EACH SIDE RETAINING;;;~;GnllUIIUU

BALL BEARING RETAINED BY ANABUTMENT AND ONE W& S RING

Walker and Schofield retaining rings M1606_0Figure 201

EFFECTIVITY: 20-09-21125 Series 1-1000 Page 202Hawker 800, 1000, 800XP Jan. 2001

Rayl~heon AircraftI25/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

2. Tools and Equipment

A. Special tools required:

Equipment/Material Part/item No.

Tool Kit 25Y1121A/B

-Chisel J72142 (contained in tool kit 25Y1121A/B)Extraction tool J72143 (contained in tool kit 25Y1121A/B)

B. Description of tools (Figure 202, Table 201)

(1) For bearings retained by one W and S ring and an abutment, each tool comprises a nut, bolt,washer, a special packing washer and, if necessary, a sleeve. Tools for bearings retained by twoW and S rings are basically the same but the packing washer is replaced by a stepped packingpiece. As the packing piece is used to support a bearing in the correct position in its housingduring insertion of a W and S ring, the packing piece step heights are varied to suit eachcombination of bearing and housing dimensions. Each side of a packing piece is identified bymeans of a suffix letter.

(2) The tool is assembled to a bearing and housing and screwed together with spanners. The nutand bolt compress the punch onto the W and S ring, forcing it into the groove of the housing, andagainst the bearing outer track.

BOLT, WASHER NUT O BOLT, WASHER NUT5) PUNCH

5) PUNCH

1) PACKING WASHERSLEEVE

PACKING

PACKING PIECE (8~ WASHER

SINGLE-GROOVE DOUBLE-GROOVEHOUSING HOUSING

M1B10 O

Assembly of toolFigure 202

C. Selection of tool (Tables 201 and202)

(1) In the case of A65Y (W and S rings are used with double groove bearings) the packing piecesare marked with the STD number of its tool and a suffix letter A or B. (Table 201)


Rayfheon Aircraft1~MHAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

(2) The side suffixed A supports the bearing while the first W and S ring is inserted, and the sidesuffixed B during insertion of the second ring. But to allow for machining tolerances, anadditional packing piece, suffixed B+.005 or 8-.005 is included with the tool and is to be used asdirected in the following text, to achieve the conditions described.

Packing pieces for use with double-groove housingTable 201

ITEM SUFFIX LETTER PACKING PIECE STEP HEIGHT

8~BL

A 0.065

B 0.035

8-.0058-.005 0.030

8+.005 0.0408+.005

M1611

(3) The table on the lid of the tool kit box relates a W and S ring to the bearing it retains and lists thepart numbers of the individual pieces making up the tool used to insert the ring. The columnsheaded 1, 3, 5 and 7 give the coding and/or part number of each piece of the tool. (Table 202)

3. Removalnnstallation of Bearings

For bearing housings, embodying W and S rings and without an axial extraction groove, the followingprocedure is suggested as a guide for W and S ring removal; individual experience may modify thesesuggestions.

A. Removal of bearing (Figures 203, 204 and 205)

(1) Split the ring with chisel J72142. Make sure the split is clean, and extends the full width ofgroove.

W.ANDS. BEARINGCOLD RING HOUSINGCHISEL

BEARINGm1607_0

Ring broken with chiselFigure 203

EFFECTIVITY: 20-09-21125 Series 1-1000 Page 204

I Hawker 800, 1000, 800XP Jan. 2001


(2) Insert extraction tool J72143 adjacent to split, and lever upwards.

EXTRACTION TOOL

W.& S.RING /JW. AND S.

RING

BEARING HOUSINGM1608 O

Ring levered up with toolFigure 204

(3) Keep the extraction tool inserted between bearing and W and S ring, and twist. Repeat thistwisting movement, around the circumference of the W and S ring to eventually force the ring outof groove. It may be convenient to grip ring with a pair of pliers to complete removal.

(4) If the W and S ring begins to break up, make a fresh start by splitting the W and S ring directlyopposite the original split, and continue the procedure.

(5) Should these methods fail, the ring may be split into several pieces and carefully moved inwardwith a chisel.

(6) Press out bearing.

W.AND S. RING

EXTRACTION TOOL \d~3 M3720Ring removed with extraction tool

Figure 205



B. Installation of bearing

(1) Single-groove housing (Figure206)

(a) Select the correct punch, bolt, packing washer and, if necessary, sleeve numbersappropriate to the particular W and S ring and bearing being installed.

(b) Press bearing into housing, until bearing outer track sits hard against the abutment of thehousing.

(c) Assemble punch to bolt.

(d) Place W and S ring on bearing.

(e) Fit bolt through bearing.

(f) Fit packing washer with recess facing inwards, and assemble washer and nut to bolt.

NOTE: If necessary; fit sleeve around bolt through the packing washer.Label on tool kit box indicates when sleeve is to be used.

(g) Screw tool together, until it just begins to clamp the W and S ring. Check that punch islocated within ring. Continue to screw tool together to force the outer periphery of the ringinto the housing groove and compress ring against bearing as far as possible.

(h) Make sure the bearing is not axially loose after insertion of ring. If looseness is apparent,remove standard ring and fit Overthick ring.

W 16(2

Insertion of W and S ringFigure 206

(2) Double-groove housing (Figures 207, 208 209 and Table 201)

(a) Select the correct punch, bolt and packing piece part numbers applicable to the special Wand S ring and bearing being installed.

(6) Press bearing into correct position in housing. The bearing outer track should be adjustedequally between grooves.



(c) Assemble punch to bolt.

(d) Place VV and S ring on bearing.

(e) Fit bolt through bearing.

(f) Fit packing piece with side suffixed A ready to enter housing and assemble washer and nutto bolt. If necessary, fit correct packing washer on packing piece.

(g) Screw tool together, until it just begins to clamp W and S ring. Check that punch is locatedwithin ring and packing piece step is inside housing. Continue to screw tool together to forcethe outer periphery of the ring into the housing groove and compress ring against bearing asfar as possible.

(h) Remove tool from component without disturbing bearing.

(i) Assemble punch to washer and bolt.

M 1613

Insertion of first W and S ringFigure 207

(j) PlaceW andSringonbearing.

(k) Fit bolt through bearing.

(I) Fit packing piece with correct side ready to enter housing and assemble washer and nut tobolt. If necessary, fit suitable packing washer on packing piece.


Ray~heon AircraftI25/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

Mlbl(

Insertion of second W and S ringFigure 208

I NOTE: (Reference Table 201.) Select correct packing piece for use during insertion ofsecond W and S ring. For example, if Item 8 side A was used in B (2)(f), then Item 8

I side B or one side of Item 9 wi/l be used. Determine the correct side to use asfollows:Insert the ~.005 side ofpacking piece Item 9 into housing and hold in with handpressure on4. Measure dimension M with feeler gauges:

If M dimension is zero (packing piece butts against housing) use the -t. 005 sideof packing piece Item 9If M dimension is between 0.0025 in, and 0.0075 in. inclusive, use side B, Item 8.If M dimension is greater than 0. 0075 in., use the -.005 side of item 9.

(m) Screw tool together, until it just begins to clamp W and S ring. Check that punch is locatedwithin ring and packing piece step is inside housing. Continue to screw tool together to forcethe outer periphery of the ring into the housing groove and compress ring against bearing asfar as possible.

(n) Make sure the bearing is not axially loose after insertion of rings. If looseness is apparent,remove standard ring and fitOverthick ring.

FIRST W. AND S. RING

BEARING

HOUSING

"M"

PACKING PIECESIDE 8+.005 Mlels_o

Packing piece selectionFigure 209



W and S ring/bearing and insertion tool dataTable 202

W S ASSEMBLED ITEM 1 (Figure 210) ITEM 3 (Figure 210) ITEM 5 (Figure 21 0) ITEM 7 (Figure 210)RING ON DRG. No.

PACKING BOLT PUNCH SLEEVE

CODE PART No. SIZE CODE PART No. CODE PART No.No. No. No.

A24Y 25081 257 P11 25Y1407 10-32 B1 25Y1415A STD419C/5315A52Y 25CW865 P11 I I UNF 814 25Y1 757/1 A STD41 90/24/5

25CW795 P11

A25Y I 25UN427 P?A 1 25Y1387/1 1 B2 2SY1417A I STD419C/54/525CF12452508124325UM953 P1D 25Y1387/7 1 I I I STD419D126/5 53 25Y1 59325UM82525UM955

A29Y 25TR275 P1B 25Y1 387/3 1/4" 1 I I STD419C/90/525WG413 I I" I UNF25WG411

A52Y 25CW443 P1C 25Y1387/5 1 I I I STD419D/2/525CW45525CW45325CW55

A66Y 25CT475 PID 25\/1387/7 1 I I I STD419D/25/525UM99325UM997

A24Y 25UN243 P4A 25Y1 393/1 83 25Y1419A STD419D/3/5 S1 25\/141325UN2472580615525802803258069452580724925FC7503

A25Y 25FT263 P3B 25\/1391/3 1 I I STD419D/26/525-6CX19A P12 25Y/1 597

A26Y 25CW505 P3A 25\11391/1 1 I I STD419C/6515 S1 25\/141325CT40725CT131 I I 1 5/16"25FC35651" 1" I UNF25CT2832508605 P48 25\113931325UM227

A31Y 25TR387 P2A 25Y1 389/1 1 I" I STD419C/92/525WG425257036925TR41725TE23525TE23725W53903 P2B 25Y1 389/325WS41 03

A35Y 2108315 P3A 25Y1391/1 1 I" I I sTD419cnlll25CX981 P4B 25\(1393/3

EFFECTIVIPI: 20-09-21125 Series 1-1000 Page 209Hawker 800, 1000, 800XP Jan. 2001

Raytheon Aircraft12S/HAWKER CHARTER 20 STANDARD PRACTICES AIRFRAME

W and S ringlbearing and insertion tool dataTable 202 (Centlnued))

W S ASSEMBLED ITEM 1 (Figure 210 ITEM 3 (Figure 210) ITEM 5 (Figure 210) ITEM 7 (Figure P10)RING ON DRG. No.

PAGKING BOLT PUNCH SLEEVE

CODE PART No. I SIZE CODE I PART No. I I CODE PART No.No. No. No.

A25Y 2565561 STD419D/4 /7 84 25Y1421/1A STD419/4/525E5561 STD419D/4/825W837 P8 25Y140125UM441 P3B 25\11391/3 1 I" I I I S2 25\1141125TR21125WG34725UM44925WS186525WB1 8525TE17725\1\1822125W8243 P4B 25Y1 393/325W8283

25\/\18187 P3B 25Y1391/325WB25

A26Y 25CX1497 I I I I" I I STD419Cn3/525CX789 P3A 25\/1391/125CX79125CX79325CX184325CX184525CX184725CF1127 I" I 1 3/8" 86 25Y1 421/1 3A STD41 9C/55/525CF1183 I" I I UNF25CF1765 I" I I 1 87 25Y1421/17A25CF99 I I I 84 25Y1421/1A25CF255125CF77525CF339 I" I I 1 85 25Y1421/9A25CW289 P3B 25Y1391M

A31Y 25CF3161 P2A 25Y1389/1 84 25Y1421/1A STD41 90/45/525081203 P2A2508182725081763 I" I I 1 87 25Y1421/17A250898925-60832925CW443 P7 25Y1 399 86 25Y1421/13A25CW90325CW69525CF913 P2A 25Y1389/1 B5 25Y1421/9AI" I S2 25\/141125UN9 P3A 25Y1391/1 1 I 86 25Y1421/13A25CX185 P2A 25Y 1 38911 1 B5 25Yt421/9A

A48Y 25UD11&12 P3B 25\/1391/3 84 25Y1421/1A STD41 90/29/5 54 25Y1 59525UD21&22

A50Y 25UN113A B P7 25\/1399A65Y 25881047 I" I" I I I" 1 STD419D/27/5 52 25\11411

25UD17&19 P3C 25Y1391/5

A67YO 25FC3577 P28 25Y1389/3 85 25Y1421/9A STD41 90/82/5


R~ylheon A~rcraft125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

W and S ring/bdaring arid insertion tool dataTable 202 (Continued)

W S ASSEMBLED ITEM 1 (Figure 210) ITEM 3 (Figure 210) ITEM 5 (Figure 210) ITEM 7 (Figure 210)RING ON DRG. No.

PACKING BOLT PUNCH SLEEVE

CODE PART No. SIZE CODE PART No. CODE PARTNo. No. No. No.

A18Y 25CF1 707 P9A 25\11403/1 89 25Y1 423/9A STD41 9(=/46/525CF98125CF1191 I I I I 88 25Y1 423/1 A25CF925 I" I I I B10 25Y1 423/1 3A25CF923 I" I 1 7/16"

UNFA18YO 25FC3577 P9A I I I 89 25Y1423/9A STD41 9(3/46/5

A1SY 25FN349 PSB 25Y1 403/3 BE 25Y1 423/1 A STD41 SC/47/5

A20Y 25FC3591 P5A 25Y1 395 B11 25Y 1425/1 A STD41 9C/48/525FC3605

A27Y 25081 367 P2B 25\11389/3 Bfl 25Y 1425/1 A STD41 9(=/56/525CW51 I" I I I I I STD4190n6/525CW417 I" I I I I" I ST0419(=/56/525CF77925CF132525CF753A/B

A38Y 25UN7 P2B 25Y1 389/3 B11 25Y1 425/1 A STD41 9C19/5112"

A50Y 25WF85 P3C 25Y1 391/5 UNFI" I" I STD419D/5/525WS37725WF41 9525\1\18221 P2B 1 25Y1389/325W818725UN11325WS1 869 P3C 25Y1391/5

A61Y 25TE243 P6 25Y1 397 B11 25Y1425/1 A STDQ1 9(=/94/5

A71Y 25CW475 P2B 25Y1 389/3 812 25Y1425/9A STD41 9C/113/5

A27Y 25CF1439 P10 25Y1 405 5/8" 813 25Y1427A STD41 9[)/6/5UNF

NOTE: Item numbers in Table 202 refer to callouts in Figure 210.

ITEM 7, SLEEVE

ITEM 3, BOLT

ITEM 1, PACKINGII

ITEMS,PUNCH iiii Mills O

Insertion tool data

Figure 210EFFECTIVITY: 20-09-21125 Series 1-1000 Page 211Hawker 800, 1000, 800XP Jan. 2001

Ray~heon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

REUSE OF SELF-LOCKING NUTSMAINTENANCE PRACTICES

1. General

CAUTION: SCRAP ANY NUT WHICH HAS OBVIOUSLY LOST ITS LOCKING QUALITIES. DO NOT

ATTEMPT TO RESTORE, OR IMPROVE, THE LOCKING TORQUE OF ANY NUT.

The following procedures concern the installing of self-locking nuts of the deformed thread type (includingcaptive self-locking nuts) and apply to internal and external use. An internal nut being defined as a nutwithin any engine casing. To avoid the possibility of self-locking nuts becoming loose or detached (whichcould result in costly damage to the engine and hazarding of the aircraft) it is necessary to make sure thatthe efficiency of the locking feature, as measured by the Locking Torque (run-down torque) is satisfactoryat the time of installation.

The measured run-down torque check, using a direct reading torque wrench, must be complied with for allnuts of self-locking, deformed thread, type used internal~, and for nuts, with a thread diameter more than 5116 inch, used externally. Nuts of this type, up to, and including 5/16 inch thread diameter, used externallymay be checked by the manual method described in subparagraph C where it is impossible to use thetorque method.

2. Tools and equipment

Equipment/Materials Part/item No.

Engine oil Item 137 (Chapter 20-95-101)

3. Check the measured runldown torque

A. Check the measured run-down torque, with a direct reading torque wrench (Table 201)

CAUTION: BOLTS WITH DAMAGED THREADS AND ROUGH ENDS ARE NOT ACCEPTABLE.

(1) Make sure that the threads of the bolt or stud are clean and undamaged and lubricated withclean engine oil (item 137) (or as detailed in the relevant instructions).

(2) Screw the self-locking nut on the bolt or stud until the bolt or stud end is flush with, or slightlyprotruding from, the nut end face.

(3) Refer to Table 201 and, using a direct reading torque wrench, check the load required to turn thenut or bolt. During this operation, make sure that the thrust face of the nut does not contact thecomponent face.

(4) Reject the nut if it has a locking torque below the value for size given inTable 201, then select anew nut and repeat the measured run-down torque check until satisfactory.



Minimum run-down locking torque for self-locking nutsTable 201

Thread size Minimum torque (Ibf. in.) Minimum torque (Nm)

No.4 UNF 0.5 0.06

No.6 UNF 1.0 0.11

No.8 UNF 1.5 0.17

No.lO UNF 2.0 0.22

1/4 in. UNF 3.5 0.40

5/16 in. UNF 6.5 0.73

3/8 in. UNF 9.5 1.07

7/16 in. UNF 14.0 1.58

1/2 in. UNF 18.0 2.03

9/16 in. UNF 24.0 2.71

5/8 in. UNF 32.0 3.62

B. Check the run-down torque manually

NOTE: This procedure is an alternative method and only applies to nut sizes up to, and including 5/isinch thread diameter in external areas where it is impossible to use the torque method.

(1) Attempt to screw the self-locking nut on the bolt or stud beyond the locking section usingmaximum finger pressure.

(2) If the nut can be screwed beyond the locking section reject it. Select a new nut and repeat thecheck until satisfactory.

4. Checks on final assembly

CAUTION: INSUFFICIENT BOLT OR STUD THREAD PROTRUSION IS UNACCEPTABLE.

A. During final assembly (after torque-tightening), check to make sure that a minimum of one full threadtin addition to the chamfered portion of the bolt or stud end) is protruding beyond the outer face of thenut.


Raytheon Aircraft Company1251HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

COMPONENT LOCKING

MAINTENANCE PRACTICES

1. INFORMATION

Bolts and nuts etc, on which the security of Class 1 structures depends shall be locked to Standard A.

Bolts and nuts etc. used on Class 2 structures shall be locked to Standard A if the nut or its bolt is in contactwith parts having relative motion such as would tend to loosen the nut.

Other bolts and nuts etc. shall be locked to Standard A or B at the designers discretion.

Standard A Locking Standard B LockingSplit pins Stiffnuts

Locking wire Double nuts locked togetherSpring locking washersTab washers

Where assembly procedures require components to be locked, select the method to be used from thefollowing general examples. Assembly procedures will define the type of locking to be used in each instanceand the general method must be adapted to suit each particular case.

2. WIRE LOCKING

Use 22 s.w.g. non-corrodible steel wire, DTD.189A for all wire-locking, except where assembly proceduresrefer to other materials.

Keep wire under tension on initial loosening of component, and stow wire ends flat to prevent damage. In fueltanks, and where possible in other areas, tuck wire ends under another wire to remove free standing sharpmetal spikes and keep electrostatic discharge hazard to the minimum.

A. Bolts and Nuts

The basic principle is to prevent a bolt or nut unscrewing, therefore the wire must be positioned so thatit tends to tighten the bolt or nut. Double wire locking as shown in Figure 201 must be used.

B. Pipe Couplings

All Fipe couplings, irrespective of their type or position in the aircraft, are to be positively locked (Ref.Figure 201). Single wire locking is permissible on pipe couplings where the wire length is short andlocated close to the component being locked. Double wire locking is preferred, and is essential wherethe connecting length of wire is unsupported andlor can be damaged. The basic principle is to prevent ajoint unscrewing, therefore the wire is to describe a helix around the joint for at least half a turn in theappropriate direction.

C. Turnbuckles and Adjustable End StrutsWire-lock to method as shown on Figure 202.

20-09-41


3. PEENING OF BOLT ENDS

CAUTION: Locking by peening can be used only when it is referenced by an assembly procedure.

When assembly procedures refer to locking by peening, cut the bolt end down to dimension A in Figure 202.A slight countersink is permissible if required, and the bolt end is then to be peened over to close one threadas close as possible to the nut. If special tools are not available, peening can be affected by using a hammerand flat punch; use a heavy reaction block to support the bolt head. It is essential to check tightness of allnuts after initial peening; follow this check by further deformation.

After locking by peening, protect peened area with treatment RF (Ref. 20-10-3527, 201).

4. SPOT LOCKING OF SCREW AND BOLT HEADS

CAUTION: Spot locking can be used only when it is referenced by an assembly procedure.

When assembly procedures refer to spot locking of countersunk screw and bolt heads, use a centre punch toburr metal from the part, surrounding the screw or bolt, or, where applicable, into each end of the screwdriverslot.

5. SPLIT PINNING

When assembly procedures refer to split pinning, use one of the following drills to suit the particular split pin,unless otherwise specified.

Bolt Size (UNF) Split Pin Drill SizeNo. 10-32 SP90C8 #51, 0.067 in. (1.70 mm)1/4 in. SP90C8 #51, 0.067 in. (1.70 mm)5/16 in. SP90C8 #51, 0.067 in. (1.70 mm)3/8 in. SP90E8 #41, 0.096 in. (2.45 mm)7/16 in. SP90E10 #41, 0.096 in. (2.45 mm)1/2 in. SP90E10 #41, 0.096 in. (2.45 mm)9/16 in. SP90G12 #30, 0.128 in. (3.25 mm)5/8 in. SP90G12 #30, 0.128 in. (3.25 mm)3/4 in. SP90H14 #20, 0.161 in. (4.10 mm)7/8 in. SP90H14 #20, 0.161 in. (4.10 mm)1 in. SP90K18 #10, 0.193 in. (4.90 mm)

6. STIFFNUT

Where stiffnuts are used, a minimum of one complete thread must project beyond the nut.Stiffnuts may be used on Class 1 applications where there are five or more bolts in a group, in which theloosening of one nut would not be catastrophic if the remaining bolts and nuts can sufficiently support theproof loads.

Jun.05~of 20-09-41

Raytheon nircraft Company1251HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

DRILL C B7A1~3

SIZE 1/4 UNF 13/16 UNFI 3/8 UNF 17/16 UNF 1 1/2 UNF BOLT No. 8 No. 10 1/4 UNF 15/16 UNF 13/8 UNF 17/16 UNFI 1/2 UNFSIZE A

A ACROSS .431 .493 .554 .679 .741DRILLB No.58 Na.SB No. 58 No. 58 No. 54 No. 54 No. 54

FLATS 438 .500 .562 .688 .750

B .365 .417 492 .604 .676DRILL No. 58 TO 8E USED FOR No. 10 PAN HEAD BOLTS AND SCREWS

DRILLC No.58 No.58 No.58 No.54 No.54

DRILLING OF NUTS FOR WIRE LOCKING DRILLING OF BOLTS FOR WIRE LOCKING

TYPICAL METHOD OF WIRE LOCKING BOLTHEADS TOGETHER (DOUBLE WIRE LOCKING)

RIGIDANCHOR

WIRE LOCKING PIPE COUPLINGS

THE BOLT END IS CUT DOWN TO DIM.A(EOUAL TO 1 1/2 THREAD PITCHES) ANDPEENED-OVER TO CLOSE ONE THREADAS CLOSE TO THE NUT AS POSSIBLE

800MINIMUM

0.15 IN. OR D/p WHICHEVER IS SMALLER

M4421

*b~

PEENING OF BOLT ENDS SPOT LOCKING OF NUTS HAOOB998104AA

Figure 201Component Locking

20-09-41

Raytheon nircraft Company125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

CONTROL CABLE TURNBUCKLES LOCKNUTS

TURNBARREL AND SCREWED ENDS

LOCKNUTS

1-

TENSION ROD AND TAPPED ENDS

LOCKNUTS

SPECIAL TURNBARREL AND SCREWED ENDSNOTE: TWISTED ENDS TO BE PUSHED INTO HOLE TO AVOID FOULING

L.H.THREAD LOCKNUTS R.H.THREAD

ii) d Y (ii

ADJUSTABLE STRUT-BOTH ENDS ADJUSTABLE

LOCKNUT

o

ADJUSTABLE STRUT-SINGLE END ADJUSTABLE

LOCKNUT

ADJUSTABLE STRUT INCORPORATING A QUICK RELEASE COUPLELOCKNUTS

M4419SPRING STRUTS OR RAMS INCORPORATING A PISTON WHICH IS FREE TO ROTATE

Figure 202Component Locking

Jun.05~f" 20-09-41

Ray~heonAircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES AIRFRAME

FLARING OF STAIMLESS STEEL TUBESMAINTENANCE PRACTICES

1. General

Flaring of tubes may be carried out using power-operated percussion, pressure equipment or hand rotaryflaring tools. The most reliable means of producing satisfactory flares i

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