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PUBLISHER.
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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
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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
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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
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
Record of RevisionsPage 1
Apr. 99
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Ray~heon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES
AIRFRAME
Revision No Revision Date Insertion Date Inserted By
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
Record of RevisionsPage 2
Apr. 99
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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
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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
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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
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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.
Letter of TransmittalPage 1 of 3
Mar.OG
-
Raytheon Aircraft Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
Ch-Se-Su Description of change
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.
Letter of TransmittalPage 2 of 3
Mar.OG
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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.
Letter of TransmittalPage 3 of 3
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.
Ch-Se-Su Description of change
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.
Letter of TransmittalPage 1 of 3
Jun.05
-
Raytheon Aircraft Company125lHAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
Ch-Se-Su Description of change
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.
Letter of TransmittalPage 2 of 3
Jun.05
-
Raytheon Aircraft Company125/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 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
Letter of TransmittalPage 3 of 3
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.
Letter of TransmittalPage 1 of 1
May 05
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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
20iLOEPPage 1 of 2
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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
20-LOEPPage 2 of 2
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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
Maintenance Practices 201
COUNTERSUNK HEAD BOLTS 20-09-141
Maintenance Practices 201
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
Maintenance Practices 201
CHEMICAL REMOVAL OF POLYSULPHIDE (Pr-tC) SEALANTS
20-10-34Maintenance Practices 201
VACU-BLASTING WITH DRY ALUMINA GRIT 20-10-40
Maintenance Practices 201
WIRING PROCEDURES AND REPAIR 20-10-50
Description and Operation 1Maintenance Practices 201
20-CONTENTSPage 1Jun.05
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Raytheon Asrcralt Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
Subject Ch-Se-Su Page
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
Maintenance Practices 201
SEALING OF PRESSURE CABINS AND AREAS OUTSIDE INTEGRALFUEL TANKS
WITH POLYSULFIDE TYPE COMPOUNDS 20-10-1002
Maintenance Practices 201
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
20-CONTENTSPage 2Jun.05
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RayNteon Aircraft Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
Subject Ch-Se-Su Page
STANDARD PRACTICES AIRFRAME continued
APPLICATION OF COLD CURING EPOXY PRIMER
TO INTERNAL AND EXTERNAL SURFACES 20-10-3527
Maintenance Practices 201
APPLICATION OF FLEXIBLE AND PERMEABLE FINISHTO AIRPLANE INTERNAL
SURFACES 20-10-3528
Maintenance Practices 201
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
Maintenance Practice 201
BONDING SILICONE RUBBERS 20-10-4005Maintenance Practice 201
BONDING RUBBER AND P.T.F.E. TO PERSPEX OR METAL 20-10-4007
Maintenance Practice 201
BONDING WITH EPOXY ADHESIVES FOR NON STRUCTURAL PARTS
20-10-4011Maintenance Practices 201
RUBBER BONDING ADHESIVE 20-10-4012
Maintenance Practices 201
BONDING WITH CONTACT ADHESIVE 20-10-4014Maintenance Practices
201
BONDING WITH SCOTCH-SEAL METAL SEALANT 2084 20-10-4016
Maintenance Practices 201
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
20-CONTENTSPage 3Jun.05
-
Rayfheoll Aircraff Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
Subject Ch-Se-Su Page
STANDARD PRACTICES AIRFRAME continued
PREPERATION OF RUBBER SURFACES FOR BONDING 20-10-9070
Maintenance Practices 201
VERY HIGH TEMPERATURE SEALANTS 20-11-1040
Maintenance Practices 201
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
CONSUMABLE MATERIALS 20-95-201
Cleaning Agents, Paint Strippers and Release Agents 1
CONSUMABLE MATERIALS 20-95-301
Adhesives, Jointing and Sealing Compounds 1
CONSUMABLE MATERIALS 20-95-401
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
-
Raytheon Aircraft Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
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
-
Raytheon Aircraft Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
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
-
Raytheon Aircraft Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
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
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Raytheon Aircraft Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
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
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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
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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
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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
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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
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Raytheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES
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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).
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Raytheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES
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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
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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)
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Rayfheon Aircraft1~MHAWKER CHAPTER 20 STANDARD PRACTICES
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(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
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Raytheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES
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(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
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Raytheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES
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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.
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(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.
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Ray~heon AircraftI25/HAWKER CHAPTER 20 STANDARD PRACTICES
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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
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Raytheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES
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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
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Raytheon Aircraft12S/HAWKER CHARTER 20 STANDARD PRACTICES
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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
EFFECTIVITY: 20-09-21125 Series 1-1000 Page 210Hawker 800, 1000,
800XP Jan. 2001
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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
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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.
EFFECTIVITY: 20-09-23125 Series 1-1000 Page 201Hawker 800, 1000,
800XP Jan. 2001
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Raytheon Aircraft125/HAWKER CHAPTER 20 STANDARD PRACTICES
AIRFRAME
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.
EFFECTIVITY: 20-09-23125 Series 1-1000 Page 202Hawker 800, 1000,
800XP Jan. 2001
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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
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Raytheon Aircraft Company125/HAWKER CHAPTER 20 STANDARD
PRACTICES AIRFRAME
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
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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
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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
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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