ASD(ENF)-TR-83-5001 DAMAGE TOLERANCE ...RECIPIENT'S CATALOG NUMBER ASD(ENF)-TR-83-5001 G.T- CE/N6...

ASD(ENF)-TR-83-5001

DAMAGE TOLERANCE

EVALUATION OF THE

ANTI-CAMOUT RIB (ACR) TORQ-SET

RECESS FASTENERS

RICHARD P. STEWART

FLIGHT EQUIPMENT DIVISION

DIRECTORATE OF FLIGHT SYSTEMS ENGINEERING

JANUARY 1983

FINAL REPORT FOR PERIOD JUNE 1981 - FEBRUARY 1982

APPROVED FOR PUBLIC RELEASE; DISTRIBUTION UNLIMITED

DEPUTY FOR ENGINEERING

AERONAUTICAL SYSTEMS DIVISION

0- AIR FORCE SYSTEMS COMMAND

8 WRIGHT-PATTERSON AIR FORCE BASE, OHIO 45433

NOTICE

When Government drawings, specifications, or other data are used for

any purpose other than in connection with a definitely related Government

procurement operation, the United States Government thereby incurs noresponsibility nor any obligation whatsoever; and the fact that the

Government may have formulated, furnished, or in any way supplied the said

drawings, specifications, or other data, is not to be regarded hy implica-

tion or otherwise as in any manner licensing the holder or any other person

or corporation, or conveying any rights or permission to manufacture, use,

or sell any patented invention that may in any way be related thereto. itThis report has been revip,,,d by the Office of Public Affairs (AS,!/PA)

arid is releaseable to the National Technical Information Service (NTIS). At I

NTIS, it will be available to the general public, including foreign nat,;nz.

This technical report has been reviewed and is approved for publication.

R. P STLWAT,' ASD/ENFEMMechanical BranchAeronautical Systems DivisionWright-Patterson Air Force Base, Ohio 45433

FOR THE COMMA• ER

-RIC E. ABELLTechnical DirectorFlight Systems Engineering

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UNCLASSIFIED3, C U R I T Y C L A S S I F I C A T I O N O F T H I S P A G E ( W " e n D ol e E n l e t e d ) R E ADI N S T R U C T I O N S

REPORT DOCUMENTATION PAGE READ INSTRUCTIONS_____________________________________ BEFORECOMPLETINGFORM

. REPORY NUMBER GOVT ACCESSION No. 3. RECIPIENT'S CATALOG NUMBER

ASD(ENF)-TR-83-5001 G.T- CE/N6 3CL4. TITLE (and Subtitle) 5. TYPE OF REPORT & PERIOD COVERED

Damage Tolerance Evaluation of the Anti- Final ReportCamout Rib (ACR) Torq-Set Recess Fasteners Tiine aR "Ri.REPORTNUBER

6.PERFORM,NC, ORG..RP1rNME

7. AUTHOR(a) 8. CONTRACT O GRANT NUMBER(s)

Richard P. Stewart

9. PERFORMING ORGANIZATION NAME AND ADDRESS 10. PROGRAM ELEMENT. PROJECT, TA'SK

AREA, & WORK UN.T NUMBERSAeronautical Systems Division (ASD/ENFEM)Wright-Patterson Air Force Base, Ohio 45433 64212F/2098 Task 5

11. CONTROLLING OFFICE NAME AND ADDRESS 12, REPORT DATE

Aeronautical Systems Division (ASD/ENFEM) J nufrv 1953Wright-Patterson Air Force B.se, Ohio 45433 13. NUMBER F PAGES

_110 •14. MONITORING AGENCY NAME & ADDRESS(If different from Controlling Office) 15. SECURITY C...ASS. (of this repor,)

UNCLASSIFIED

15a, DECL ASSI'FICATI ON/DOWN GRAOIN GSCHEDULE

"16. DISTRIBUTION STATEMENT (of thli Report)

Approved for public release; distribution unlimited.

I7. DISTRIBUTION STATEMENT (of the abstract entered in Block 20, It different from Report)

IS. SUPPLEMENTARY NOTES

Jack HoffmanASD/ENF/STINFO

19. KEY WORDS (Continue on reverse side if necessary and Identify by block number)

Recess Fasteners Torx RecessTorq-Set RecessAnti-Camout Rib Recess Torq-SetDamage ToleranceACR Recess

"20. ABSTRACT (Continue on reverse side If nccssary end Identify by block number)

"NThis report describes the latest effort in the continuation of the Air Force'stechnical evaluation of aerospace fastener recesses. Earlier work had inves-tigated the prototype Anti-Camout Rib (ACR) recess design, i.e., one rib oneach removal wall of the recess and the driver bit. This test program, at therequest of the Secretary (if Defense, evaluated the production configurationwith-multiple horizontal ribs on each removal wall of the driver bit and onevertical rib on each removal face of the fastener recess. I

DD J 1473 EDITION OF 1 NOV 65 IS OBSOLETE UNCLASSIFIEDSECURITY CLASSIFICATION OF THIS PAGE (W1?en Dae iLThterad)

UNCLASSIFIEDSECURITY CLASSIFICATION OF THIS PAGE(W NI Date l. d) - -

This effort was confined predominantly to the damage tolerance testing of the,following recess/driver bit combinations: (a) standard Torq-Set recess andstandard Torq-Set driver bit, (b) ACR Torq-Set recess and ACR Torq-Set driverbitI (c) ACR Torq-Set recess with standard Torq-Set drivei bit and (d)standard Torq-Set recess with ACR Torq-Set driver bit. Limitea tests of theTorx recess fastener modified with 5 taper on the side wall of the recess were

also conducted. This test program was coordinated with and approved by theArmy and Navy.

Besides the testing of the recesses, this effort was expanded to determine thecost and service benefits of the Anti-Camout Rib on the Torq-Set recess.-'

-he te.L LISUItS, as well as the cost sLudies, indicate that the ACR Torq-SeLrecess combined with the ACR Torq-Set driver bit demonstrated best overallperformance of the four combinations, while the ACR Torq-Set recess with stand-ard Torq-Set driver bit and the standard Torq-Set recess with ACR Torq-Setdriver bit. combinations offered some improvement when compared to the standardTorq-Set rLcess and standard Torq-Set driver bit combination. All combinationsof standard and ACR Torq-Set recesses and driver bits were found to be fullyinterchangeable.

UNCLA-SI FTED

.EC•JU ITY CLASSIFICATION OF i is r AOGE•Whr- f P.-. no )

FOREWORD

This report describes an in-house evaluation conducted by personnel of

the Aeronautical Systems Division and the Wright Aeronautical Laboratories,

Flight Dynamics Laboratory. In the Aeronautical Systems Division, the work

was carried out under Program Element 64212F, Project 2098, Task 5.

The work reported herein was performed during the period of I June 1981

through I February 1982, under the direction of the author, Mr. Richard P.

Stewart.

The author wishes to thanK Messrs Jack Smith and Larry Bates who were

responsible for conducting the tests; Mr. Harold Stalnecker for providing

support and technical guidance; Messrs Juan Acaron and Gene McPherson for

their computer programming and data analysis; and Mr. Augustin Sanchez, Miss

Mary Ann Rotterman, Miss Shawn Hall, and Mrs. Cathy Kibler for their

assistance in the preparation of the report.

Major Maynard Ford of ASD's Life Cycle Cost Management Division contri-

buted to Section VII, Cost Analysis.

The following companies are owed a special debt of gratitude for pro-

viding the test samples and their technical support:

Air Industries Corporation

Apex Machine and Tool Company

Defense Logistics Agency/Defense Industrial Supply Center

General Dynamics Corporation

Grumman Aerospace Corporation

Phillips Screw Company

iii

VIA

TABLE OF CONTENTS

SECTION PAGE

I INTRODUCTION I

II TEST PLAN 4

III TEST EQUIPMENT 7

IV TEST APPROACH/PROCEDURES 17

V TEST RESULTS 23

VI DISCUSSION OF TEST DATA 26

VII COST ANALYSIS 52

Vill SERVICE EXPERIENCE 55

IX CONCLUSIONS 57

X RECOMMENDATIONS 58

APPENDIX 59

Observers of Testing, Lot Identification,

Raw Data, and Distribution List

II

j-,jCL~j4G ppA IAI&NOT I~b

vi

LIST OF ILLUSTRATIONS

FIGURE PAGE

1 Styles of Recesses Tested 2

2 Phillips Torque Measurement and Test Fixture 8

3 In-House Test Fixture and Data System 9

4 Calibration of In-House Fixture with Load CeHl 11

5 First Run Calibration Check 13

6 Second Run Calibration Check 14

7 Third Run Calibration Check 15

8 Fourth Run Calibration Check 16

9 Recess Inspection Gages 22

10 .190 Inch Diameter Torque Test of Torq-Set Recess @ 0' 33

Driver Offset and 20 lb End Load

11 .250 Inch Diameter Torque Test of Torq-Set Recess @ 00 34


12 Average of First and Second Torque Effort for .190 Inch 35

Diameter

13 Average of First and Second Torque Effort for .250 Inch 36

Diameter



15 .IS0 Inch Diameter Torque Test of Torq-Set Recess @ 00 38




vi

17 Removal Torque Vs End Load Plot of .190 Inch Diameter, 40

First Effort, Std/Std Condition


Second Effort, Std/Std Condition


First Effort, Rib/Std Condition


Second Effort, Rib/Std Condition

21 Removal Torque Vs Recess Conditions and Material 44

Combinations, .190 Inch Diameter

22 Removal Torque Vs Recess Conditions and Material

Combinations, .250 Inch Diameter 45

23 Removal Torque Vs End Load for Modified Torx Recess, 46

.190 Inch Diameter

24 Removal Torque Vs End Load for Modified Torx Recess, 47

.250 Inch Diameter

25 Removal Torque Vs Offset Angle for Modified Torx Recess, 48

.250 Inch Diameter

26 Photographs of Test Specimen Number 0103 and 0104 49





vii

[r

GLOSSARY OF TERMS

Camout - The application of torque to a recess until a complete disengage-

ment occurs between the bit and the recess. This torque application usually

damages the recess, bit, or both, depending on the type of recess, end load,

etc.

End Load - The force with which the bit is pressed into the recess while

removal or installation torque is applied.

Freezing - When a fastener is installed and cannot be removed with con-

venient tools and bits.

Off-Angle - The angular offset or misalignment between the axis of the screw

and the axis of the bit.

Seizing - Similar to freezing, but usually due to a material incompatibility

and/or lack of sufficient lubricant to allow normal removal.

Shear Head - A fastener with a smaller than "normal" head which is used

wheie shear Furces arc v.tedorina,,t. Usually tile nedd is the same as the

head of the next smaller shank diameter tension head fastener.

Tension Head - The "normal" dimensioned head size which is used where both

shear and tension forces can cause failures.

Torg-Set - An offset-cruciform recess, readily forged in fastener heads, the

planform in which the four driving faces intersect at a common point. A

registered trademark product of the Phillips Screw Company.

Anti-Camout Rib Torq-Set - Similar to the Standard Torq-Set recess except

includes a single vertical rib on the removal walls or faces of the fastener

and multiple, horizontal ribs on the removal sides or walls of the driver

bits. During removal, the ribs interlock and provide an anti-camout

feature. A proprietary and registered trademark product of the Phillips

Screw Company.

viii

T--Wing A three wing conical design with a center radius which acts as a

drill center to facilitate drillout. A proprietary and registered trademark

product of the Phillips Screw Company.

Torx - A vertical walled, flat, or round bottom rezess with six rounded

lobes used as the driving surfaces. Since the walls are vertical, no end

load is required. Torsional forces are reacted through a larger area than

points or corners. A proprietary and registered trademark produict of Camcar

Division of Textron Company.

ix

ixA

SECTION I

INTRODUCTION

The test effort described and discussed in this report is a continuation

of the Air Force's technical evaluation of aerospace fastener recesses.

Previous work was reported in ASq-TR-78-5 and AFFDL-TR-78-22. The earlier

work had investigated the prototype ACR design, i.e., one horizontal rib on

each removal face of the driver hit and one vertical rib on each remuval

face of the fastener recess. This program evaluated the final confiouration

of multiple horizontal ribs on each removal face of the driver bit and one

vertical rib on each rerioval 1ace of the fastener recess.

This technical effort Was confined to the damage tolerance testing of

the Torq-Set and ACR Torql-Set recess fasteners, and li-niten tests of the

Torx recess fastener modified with 50 taper on the side wails of thýe recess

to provide improved offset driver/ bit engagement. These recesses are shown

in Figure 1.

Subsequent to the initiation of the planning for this program, the

Secretary of Defense directed the Air Force to take the lead in getting a

coordinated test plan established to resolve whether or not the Department

of Defense (DOD) should standardize on the ACR Torq-Set recess fastener.

This effort was therefore expanded to also encompass the cost henefits of

the Anti-Camout Rib feature on the 'orq-Set recess. The test program con-

sequently gained a high level of interest as reflected in the list of orga-

nizations shown in the Appendix whose personnel observed or participated in

sore segments of the testing. This test program was coordinated with and

appro'•-d by the Army and Navy.

Ihis eva uation examined one particular design feature, i.e., determine

°1

MS 33>6 5 !iO ToOR-SE T RLCE"SS

MS14 91 NTICAM-!ýT RIB (A~t) T RQ,.-;Il PCES

NA 80 OIUI NXRCS

Fiue . Sylsoficss- Tse

*~2

the damage tolerance attributes, if any, of the Anti-Camout Rib Recess in

the Torq-Set fasteners. A fastener system selection should not bo' predi-

cated solely upon the results presented in this report but should addition-

ally consider the performance characteristics of the candidate fasteners for

the intended application. Design characteristics such as tensile strength,

shear strength, bending strength, fatigue, application environmental effects

such as corrosion tolerance, clean-out capability, and other adverse condi-

tions such as paint in the recess, off-angle drive, wrong size driver bit,

etc. must be evaluated in consonance with the specific application.

I

.1

3

SECTION II

TEST PLAN

The testing was conducted in accordance with the following test plan,

coordinated with Air Force Systems Commiand, the Army and the Navy.

Test Requirements for Torque Testing the Anti-Camout Rib (ACR)

Feature of the Tor -Set Recess to MIL-STD-1761.

1. A first torque followed hy a secnnd torque using one driver bit/one bolt

when possible, shall be tested. If the driver bit breaks, another one shall

he used in its place even if it happens between first and second torque.

The test procedures of Air Force MIL-STO-1761 are to be followed.

2. Combination of recess configuration vs recess driver in order of

priority:

a. Ribbed recess vs ribbed driver

b. Standard recess vs ribbed driver

c. Ribbed recess vs standard driver

d. Standard recess vs standard driver (for control)

3. Size of bolts to be tested in order of priority:

a. 0.190 inch diameter

b. 0.250 inch diameter

4. The bolts shall be made from the following material:

a. Cadmium plated alloy steel 160-180 KSI

). A-286 Cres steel 160-18,0 KSI

5. The following end load shall be applied:

a. 20 lbs for 0.190 inch diameter

b. 40 lbs for 0.?50 inch diameter

6. An offset angle of 0o shall be used.

4

7. The recess shall be unpainted and the driver bits new.

8. Dimensions for the ribbed driver bits and recesses shall be

specified. (Phillips Co. drawings)

Note: A minimum of five specimens are to be tested for each case.

(Per MIL-STO-1761)

9. Number of specimens to be tested:

Test Matrix: Recess, specimens Driver bit, specimens

Rib, 7 Rib, 7

Std, 7 Rib, 7

Rib, 7 Std, 7

Std, 7 Std, 7

For two materials, two shank diameters, tension head bolt

# of Bolts # of Bits

Std Rib Std Rib

0.190 in. dia. 14 14 14 14

0.190 in. dia. 14 14 14 14

(0.250 in. dia. 14 14 14 14

0.250 in. dia. 14 14 14 14

Note: Shear head bolts may be tested later using the same specimen

breakdown.

The following deviations from the established plan were required:

1. Limited 40 offset angle testing was accomplished in addition to the

0O offset angle testing.

2. Five test specimen replicates in lieu of seven replicates were

tested due to limited supply of fasteners.

•. With few exceptions, a new driver bit was used for each torque

-- ., 5

application.

4. Ten lbs end loads were applied to the .190 inch diameter fasteners;

20 lbs end load were applied to the .190 and .250 inch diameter fasteners;

40 lbs end loads were applied to the .190 inch diameter fasteners.

6

SECTION III

TEST EOUIPMENT

Two separate pieces of test equipment were used in this test program to

accomplish the testing in a relatively short time period. A modified

Sturtevant Torque Test Fixture Model TTF-1/2 was borrowed from the Phillips

Screw Co. The modification consisted of the addition of bearings in lieu of

the hand crank to allow for vertical travel as well as torsional rotation.

Various end loads were applied vertically to allow unrestrained camout.

Fixed wedge blocks easily slid under the Screw holding fixture to provide

the desired offset angle for torque application. The test machine is shown

in Figure 2. The electronic torque wrench used on top of the axial spindle

"-was a GSE Model 1140-50 serial No. 044, capacity 0-600 lbs - in. calibrated

on 6 January 1979. The data was observed on a peak holding, five memory

indicator-recorder, GSE Model 229-D, serial No. 1121, calibrated on 20

January 1980. All the data was recorded by the Flight flynamics Laboratory

computer data acquisition system.

The other piece of test equipment was the AFWAL/FDL designed and built

machine described in the reports referenced in Section 1. This test machine

shown in Figure 3 was specifically designed for recess testing. The machine

simulates in the laboratory the hand held speed handle used in the field.

This machine employs an off-the-shelf speed handle driven by a lead screw

through a nut and connecting rod. The lead screw is turned by a reversible

1/15 hp electric motor, Torque is measured by a strain gage extension on

the speed handle. An electronic cnntrol box allows torque limits to be set

in either clockwise or counterclockwise directions. A cycle counter is also

included. Torque was measured on a digital voltmeter calibrated to read

7

rj

71~9

directly in inch-pounds; an oscillograph also monitored the torque applica-

tions. With the butt end of the speed handle mounted in a rubber block,

flexibility encountered in service applications was simulated. The base of

the equipment holding the handle was adjustable to allow an offset angle to

be introduced. The protractor to measure the offset angle can be seen in

Figure 4. End load is applied by a mechanical dead weight acting through a

cable, pulley, and bell crank system. The weight is reacted by the fastener

mount. The mount is hinged at the four corners to allow horizontal motion

and permit the fastener to be backed away from the driver. This was done to

duplicate the driver camout action. The fastener itself was held between

two hardened steel blocks with a vee groove in each block. The blocks were

firmly clamped together with two 3/8 inch diameter hex head bolts to prevent

rotation. This allowed a pure reces: investigation without any influence

from torque/tension relationships, thread fit, lubricants, etc. The actual

end load was measured prior to mating the fasteier and driver. This was

accomplished by inserting a load cell in the holding fixture as shown in

Figure 4. The data recorded with the test equipment was found to be com-

parable to those obtained with the hand held -'%--d handle but parameters

such as end load, angle, and torque could now be closely controlled with the

person taken out of the loop. This test method was designed to (a) measure

the torque applied to a recess by a driver bit; (b) allow a preset constant

end load to be applied and (c) allow a preset bit offset with the driver and

recess engaged. As with the modified Sturtevant machine, the torque data

was measured by a strain gage on the adapter next to the driver bit and fed

into the same data acquisition system. Since two separate test machines

were utilized, calibration curves were developed for data correlation.

10

-set Se

L0

Figures 5 through 8 are the calihr'a.ion curves for both test machines. The

channel numbers 6 and 7 correspond to the modified Sturtevant machine and

the AFWAL/FDL machine, respectively, and are the data channels used in the

Flight Dynamics Laboratory computer. As can be seen, very good correlation

was maintained from 0 in-lb to 450 in-lb with three different operators, one

laboratory technician, one Air Industries Corporation representative, and

one Phillips Screw Company representative.

12

SCREN TESTS (FIRST RUN)LARRY BATES

500.0

4.5f30. 0

3400.0 -

L,Z

-) 2350.0

200.01300.0

I.-

- 250.0Cr')

co 200.01

03 150.0

1.00.0

50.0

0.0 -50.0 -iOO.0 -150.0 -200.0 -250.0 -300.0 -350.0 -400.0 -450.0 -500.0IN. LBS. f7) (HFNAL MACHINE)

Figure 5. First Run Calibration Check

13

SCREW4 TESTS (SECOND RUN)LARRY BATES

500. 0

450.0

- 400.0Lizn-7L-) 350.0

Z 300.0

Li

7 250.0Co

200.0

CO

I 150.0-J

-. 100.0-

50.0

0.0 -50.0 -100.0 -150.0 -200.0 -250.0 -300.0 -350.0 -400.0 -450.0 -500.1

IN. LBS. (7) (RFNAL MACHINE)

Figure 6. Second Run Calibration Check

14

SCREN TESTS (ThIRD RUN)ED B9!JMG9RTEN

500.9

4.5o. 0 -1

L)" 1

CD 250.0

S200,9

250.01I

CD 100.9

50.9

0.00.0 -50.0 -100.0 -150.0 -200.0 -250.0 -300.0 -350.0 -400.0 -450.0 -500.0

1N. LBS. (7) (RFWAL M9CHINE)

Figure 7. Third Run Calibration Check15

SCPE Tý5TS IrpOjPflI PJN)

- EP r~~1

1 11

z

Figur 8. Fut1u airto hc

cr-

U "'U *O I1c~ A

IC

5, 2 Q1 "-'

IN 2. 71[A4A7 HC!N

Figure 8. Fourth Run Calibration Check

SECTION IV

TEST APPROACH/PROCEDURES

As indicated in previous investigations, the Aeronautical Systems

Division pioneered the development of "damage tolerance" recess testing.

This proocedure is basically a method to conduct in the laboratory a

realistic test of conditions which exist in the field. Damage tolerance is

the capability of the recess/ bit combination to transmit torque after some

degree of damage. The test procedure is well documented in MIL-STD-1761

(USAF). The testing concept is to achieve a "camout" failure where the

driver bit rides up and out of the recess, a new bit is installed and the

torque is applied to failure a second time. The amount of torque obtained

in this second effort is viewed to be critical with regards to field perfor-

mance of the wrenching system.

It is expected that once a failure has occurred, the remaining capabi-

lity of the recess/bit combination would be less than when new. f the

second torque value to failure is less than that required for removal, the

mechanic would not be able to remove the fastener. The delta torque between

the first and second torque values to failure is a measure of the "Damage

Tolerance" of the recess design. For a relatively small delta, one would

conclude that the recess performance was one that degraded slowly. This

design feature is highly desirable since it allows the best chance of remo-

val of the fastener even though it had incurred some recess damage during

the first removal attempt. A recess design that offers a significant torque

capability to second failure would be of greater practical utility because

fastener removal would be more likely.

17

The specific test procedures were as follows:

1. Load the fastener into the blocks and secure

2. Install proper driver bit into Appropriate adapter

3. Mate the driver bit with the ecess

4. Introduce angular offset when required

5. Apply appropriate dead weight to simulate the end load

6. Apply torque wrench

7. Take calibration readinq before each set

8. Apply smooth torque in the counterclockwise (removal) direction

until ultimate failure. Failure is defined as cawout, bit

breakage, complete load loss or any combination of these failure

modes.

9. Remove driver bit and any bit particles which may be in the recess

10. Install a new driver bit into adapter

11. Repeat steps 3 through 9

End Loads

The end loads used in this test program were 10, 20, and 40 lbs. These

values were arrived at from data previously gathered in extensive field sur-

veys. The 20 lbs end load was the predominant test load since it was the

most common end load observed. Where sufficient test specimens were

available, tests were also conducted at 10 and 40 lbs.

Driver Offset

Two offset angles were used, QL and 40. The 40 offset from the perpen-

dicular was also determined from previous field surveys to be an average

offset angle. Again, the predominant number of tests were conducted at 00,

with 40 offset where sufficier,_ specimens were available.

18

Driver/Bit Test Combinations

Five separate driver/bit combinations were tested:

(1) Standard Torq-Set driver bit and a standard Torq-Set recess

fastener (STO-STD)

(2) Ribbed Torq-Set driver bit and a ribbed Torq-Set recess

fastener (RIB-RIB)

(3) Standard Torq-Set driver bit and a ribbed Torq-Set recess

fastener (STD-RIB)

(4) Ribbed Torq-Set driver bit and a standard Torq-Set recess

fastener (RIB-STD)

(5) Torx driver bit with modified Torx recess fastener

The standard Torq-Set driver bit/standard Torq-Set recess fastener com-

bination was included as the base line since it is widely used on military

aircraft. The ribbed Torq-Set driver bit/ribbed Torq-Set recess fastener

combination was included since it is purported to be the most effective com-

bination. The standard Torq-Set driver bit/ribbed Torq-Set recess fastener

and the ribbed Torq-Set driver bit/standard Torq-Set recess fastener com-

binations were included lor two reasons. First, to isolate any changes in

torque capability to either the ribbed Torq-Set driver bit or the ribbed

Torq-Set recess fastener. Second, to represent a transitional situation

wherein the ribbed Torq-Set driver bit may be used in the field in conjunc-

tion with the standard Torq-Set recess fastener, or the standard Torq-Set

driver bit in conjunction with the ribbed Torq.Set recess fastener.

Torque Efforts

As explained above, for each fastener specimen two torque efforts per

MIL-STD-1761 were applied using a new driver bit for each application.

19

Test Fasteners

The fasteners tested were of two diimeters, 0.190 (#10) and 0.250 inch.

These represent the majority of removable screws used on aircraft, and the

most easily over-torqued fasteners.

Since this was an expedited test program, production Torq-Set fasteners

were obtained from numerous sources such as Grumman Aircraft Corporation,

General Dynamics, Fort Worth Division, Air Industries Corporation, and The

Phillips Screw Company. Some standard Torq-Set fasteners were also obtained

from Base Supply at Wright-Patterson Air Force Base, Ohio. The modified

Torx recess fasteners and necessary driver bits were supplied by Air

Industries Corporation. The number of Torx fasteners tested was limited by

the few driver bits supplied by Air Industries Corporation. Additional Torx

driver bits were obtained from Apex Machine and Tool Company.

For most test conditions, at least five separate identical fasteners

from the same lot were used for each first and second torque effort

totalling 10 tests for each test set. Eighteen separate lots of Torq-Set

fasteners and two lots of Torx fasteners were tested. A summary of the test

specimens is included in the Appendix.

Driver Bits

Three lots of .190 inch diameter driver bits and two jots of .250 inch

diameter driver bits for the Torq-Set fasteners were used. A very limited

number of modified Torx driver bits were available which therefore limited

the number of Torx fasteners tested. A summary of the driver bits used in

the test program is included in the Appendix.

Gaging and Inspection

All the Torq-Set fastener lots were randomly sampled in accordance with

20

MIL-STD-105D, inspection level S-2, Acceptable Quality Level (AQL) of 2.5,

and the recesses inspected. The gages consisted of depth penetration dial

gages and go/no-go plug gages to measure the recesses wall angles and "wing"

width. The gages used are shown in Figure 9. The inspection criteria of

MS33781 and MS14191 were applied to the standard Torq-Set and ACR Torq-Set

fastener recesses, respectively. Recess gages and inspection criteria for

the modified Torx recess fasteners were not available.

Gages to measure the driver bits blade wear and deflection were not

available to determine whether or not the driver bitb' critical dimensions

remained within specification limits. Therefore, a new driver bit was used

to each torque application.

21

SECTION V

TEST RESULTS

The sumnmary of the raw test data is tabulated in Table A-i in the

Appendix. This data is grouped in sets of ten tests corresponding to two

torque applications for each of five replicates. The summary identifies the

fastener size, driver bit/recess combiration, end load, driver/recess offset

angle, highest torque attained, condition at highest torque, lot identity,

fastener material, and test machine used. For each group of ten tests, the

minimum, maximum, and average torque sustained are summarized for both first

and second efforts. The test results are presented in bar chart format for

the five driver bit/recess fastener combinations tested. All data com-

parison is referenced to the standard Torq-Set driver bit/standard Torq-Set

recess fastener combination since it is widely used in military aircraft

applications.

Figure 10 shows the maximum, minimum, and average torque values for the

first and second torque applications at 20 1bs.end load for the .190 inch

diameter fasteners.

Figure 11 presents the same data except for the .250 inch diameter

fasteners.

Figures 12 and 13 are the summa ries of the average of the first and

second application torque values for the .190 and .250 inch diameter faste-

ners respectively with 20 lbs end load.

Figure 14 depicts the test results with reduced number of test specimens

at 40 driver offset.

Figure 15 is the summary of the maximum, minimum, and average torque

values for the first and second torque applications at 10 lbs end load for

23

the .190 inch diameter fasteners.

Likewise, Figure 16 shows the comparable data at 40 lbs end load.

Figures 17 and I1i depict the data of the average torque values for first

and second torque applications respectively, regardless of the applied test

end loads for the .190 inch diamete," standard Torq-Set driver bit/standard

Torq-Set recess fastener combination.

Figures 19 and 20 present the comparable data for the ACR Torq-Set

driver bit/standard Torq-Set recess fastener combination.

The effects of the base material and/or coating on torque values are

shown in Figures 21 and 22. These figures summarize tne results for the

.190 and .250 inch diameter fasteners respectively, at 20 lbs end load com-

paring stainless steel and cadmium plated alloy steel fasteners. The stan-

dard Torq-Set bit/standard Torq-Set recess fastener combination is compared

with the ACR Torq-Set driver bit/standard lurq-Set recess fastener combina-

t iota.

Figures 23, 24, and 25 show the results of the tests with the limited

samples of modified Torx recess fasteners and driver bits.

A summary of the fastener recess and driver bit failure modes is pre-

sented in Table 1.

24

TORO-SET RECESS TESTS

NUMBER OF TESTS IN EACH CATEGORY AND TOTALS

DIA EFFORT FAILUkE ------- BIT-RECESS COMBINATION- ...... TOTALS

INS MODE STO-STO RIB-RIB STD-RII RIB-STD

.190 1 CO 113 26 '40 75 254

.190 1 BB 2 19 0 50 71

.190 2 CO 114 36 40 q4 2B84

.Iqo 2 B 1 7 0 26 34

.250 1 CO 55 3 10 22 100

.250 1 BB 0 5 0 13 18

.250 2 Co 55 7 10 "1 113

.250 2 8B 0 1 0 3 4

TOTAL 878

STD-STD - STANDARD BIT - STA- RD RECESS

RIB-RIB - ACR BIT - ACR RECES,,

STO-RIB 9 STANDARD BIT - ACR ý.r.CESS

RIB-STO - ACR BIT - STANDARD RECESS

FAILURE MODEt CO - CAM OUT - B - BROKEN BIT

TESTS RUN IN JUNE-AUGUST 1981

TABLE I. SUMMARY OF FAILURE ,lODES IIISI

251

SECTION VI

DISCUSSION OF TEST DATA

General

The torque capabilities of fasteners are influenced to a great extent by

the interface and interaction of driver bit and fastener recess. The per-

formance of any recess can materially be affected by wear, paint, shallow

penetration, driver bit deflection, blade corner wear and incorrect blade

angle. Coupled with the critical physical parameters, the quality control

of the fasteners also has a significant effect upon the torque capability of

the recess. Two of the most significant parameters which reflect upon the

quality of the fasteners are the blade or wing width and penetration. The

penetration depth varies from lot to lot and is attributed to header tool

wear. Furthermore, most screw manufacturers do not produce fasteners with

maximum recess depth in order to avoid critical screw failures. Therefore,

fasteners with recesses within the median tolerance range depth penetration

are far more prevalent than fasteners with maximum depth recess penetration.

No specific correlation was made between recess depth and performance.

Contributing to the degradation of the quality of the recesses is the wear

of the punch or header tooling beyond limits, resulting in shallower

recesses. The random inspection of ACR Torq-Set fastener lots indicated

that the fastener recess conformed to the criteria of MS14191. The random

inspection of the standard Torq-Set fastener lots however revealed that not

all the fasteners in several lots conformed to the criteria of MS33781.

However, in spite of the fact that under a stringent quality control program

these lots would have been rejected, these fasteners were none-the-less used

in the test program since they were "off-the-shelf" fasteners and represen-

26

tative of the hardware used in the field. The majority of the testing was

performed on .190 inch diameter fasteners at an applied end load of 20 lbs

at 00 driver offset. Fewer tests were performed at other end loads and

driver offset angles; comparable number of tests were not conducted on the

.250 inch diameter fasteners due to the disparity in available test speci-

mens.

The wide scatter of data between the maximum torque attained on the

first torque application and the minimum torque attained on the second

torque application is attributed to driver/recess interface fit and was

aggravated by substandard quality recesses found in the lots of Government

inventory off-the-shelf fasteners used in the evaluation. The recess mini-

mum torque requirements listed in Table III of MIL-B-87114A, "Bolts, Recess

Drive, General Specification for" formed the basis of comparison for the

observed torque values. The reference data is shown in Figures 10 through

25.

Data Analysis

Figure 10 shows that for the .190 inch diameter fasteners the perfor-

mance of the rib-rib and the rib-std combinations exceeded the base line

std-Std at 00 driver bit offset and 20 lb end load combination. The torque

band between the minimum and maximum torque values was narrow, resulting in

an average torque value higher than the std-std combination. Even though

the torque band between minimum and maximum torque on the second effort was

greater when compared to the std-std combination, the average torque capabi-

lity on the second effort exceeds the comparable value for the std-std com-

bination. For the rib-std combination, the torque band between minimum and

maximum torque on the first effort exceeded the same band for the std-std

27

combination although the average torque on the first effort exceed the com-

parable average for the std-std combination. On the second effort, the

average torque for the rib-std combination is slightly higher than the std-

std combination but lower than the rib-rib combination. As can be seen from

Figure 10, the performance of the std-rib combination is comparable to the

std-std combination but poorer than either the rib-rib or rib-std com-

binations.

Figure 11 represents the same trend for the .250 inch diameter fasteners

as did Figure 10 for the .190 inch diameter fasteners under the same con-

ditions. The rib-rib combination showed an improvement in the average

torque capability for both first and second effort when compared to the std-

std combination. In both combinations, the torque band between minimum and

maximum values was considerably wider for the second effort than first

effort. For the rib-std, the torque band between the minimum and maximum

torque values for the first effort was of higher magnitude than the rib-rib

combination. The torque band was even wider for the second effort but the

average value exceeded the std-std combination but was less than the rib-rib

combination. The performance of the std-rib combination exceeded the per-

formance of the std-std comoination.

Figures 12 and 13 indicate that for 00 driver bit offset and 20 lbs end

load the combined first and second efforts average torque values for the

rib-rib, rb-std, and std-rib combinations exceed the combined first and

second effort average torque capabilities uf the std-std combination. The

trend of the data is consistent for both the .190 and .250 inch diameter

fasteners; the torque capability improvement in descending order is rib-rib,

rib-std, std-rib, and std-std combinations.

28

Figure 14 presents the torque capabilities for the .190 inch diameter

fasteners with driver bit offset of 40 and 20 lbs end load. The first and

second effort torque values are essentially comparable with the rib-rib com-

bination showing a slight improvement.

Figure 15 depicts the torque data for the .190 inch diameter fasteners

at 0* driver bit offset with an applied end load of 10 lbs. Ihe average

first effort torque values were comparable for the four driver bit/recess

combinations. The average second effort torque values for the std-std and

std-rib combinations were comparable and lower than the first effort average

torque values. The average second effort torque values for the rib-rib and

rib-std combinations were lower than the other two combinations.

Figure 16 shows the results of the measured torque values for the .190

inch diameter fasteners at 0' driver bit offset and end load of 40 lbs. flue

to the limited number of test specimens, only the std-std and rib-std com-

binations could be compared. The first effort torque values for these com-

binations were comparable. However, the second effort torqi:e values for the

std-std combination exceeded the values for the rib-std combination.

Figures 17, 18, 19, and 20 show the effects of end loads upon removal

torque. For the first efforts no significant difference was observed when

comparing the std-std combination with the rib-std combination (Figure 17

vs. Figu-e 19). Likewise, on the second efforts no significant cifference

was observed when comparing the std-std combination with the rib-std com-

bination except at the 40 lbs end load (Figure ", vs. Figura 20). The lower

removal torque was attributed to the fact that the test specimens came from

a lot that failed to meet the recess inspection criteria of MS33781. The

depth of the recesses was shallower than required. This condition, coupled

29

with the recess damage induced during the first effort accounted for the low

removal torque at the 40 lbs end load condition. Lack of sufficient faste-

ners precluded comparable anaiyses of the effects of end loads for the std-

rib and rib-r½b combinations.

Figures 21 and 2? depict how the torque values are influenced by the

material/coating of the recess. For the .190 inch diameter fasteners and

the std-std combination, the first effort average torque values presented in

Figure 21 for the cadmium plated alloy steel and A-286 stainless steel

fasteners were comparable; however for the second efforts, the torque values

for stainless steel fasteners were lower than those for the cadmium plated

fasteners which was contrary to expectations. The cadmium plating normally

acts as a lubricant between the fastener and driver, caming out at relati-

vely lower torque values. For the rib-std combination, the first effort

average torque values were also comparable for both material fasteners.

Likewise, the second effort average torque values exhibited the same trend

as seen in the std-std combination. Figure 22 shows the comparable

materials effects for the .250 inch diameter fasteners. The first effort

average torque values for the std-std combination for both materials were

comparable with the stainless steel fasteners being slightly higher. The

second effort torque values followed the same trend as that exhibited for

the .190 fasteners. For the rib-std combination, the first effort average

torque values were again comparable. The trend for the second effort

average torque values however was reversed from that seen for the std-std

combination and the .190 inch diameter fasteners; i.e., the second effort

average torque values were higher for the stainless steel fasteners than the

cadmium plated fasteners.

30

Figures 23, 24, and 25 present the test results for the modified Torx

fasteners. These fasteners consistently exceeded the MIL-9-87114A reference

data torque values for the first efforts for both the .190 and .250 inch

diameter fasteners at 20 aid 40 lbs end loads, 0o and 40 driver hit offset,

using either of two manufacturers driver bits. The second effort average

torque values for the .190 inch diameter Torx recess fasteners also met or

exceeded this reference datum at 0lo driver bit offset for the end loads and

driver bits shown in Figure 23.

Failure Mode Analysis

In recess damage tolerance testinig, the first failure mechanism observed

is recess "tear-out" where the entire recess wall is not only deflected hut

also suffers a bearing failure. This results in a ramped surface which can

extend from the bottom of the recess to the top of the head surface.

Recause of this ramp, second effort attempts result in catastrophic fail.ires

of the recess and/or bit, sometimes with virtually no remaining torque capa-

bility. This was evident during this test program where very high first

effort torque values were obtained followed by very small torque values

during the second effort at the same end loads. The second failure mechanism

which was frequently observed with the ACR Torq-Set system, manifested

itself in either driver bit breakage or severe permanent torsional deflec-

tion of the driver bits. This was attributed to the recess consistently

exceeding the rated strength of the driver bits. II

Figures 26 and 27 show typical ACR Torq-Set driver bit fracture

fail ures.

Figure 28 shows typical ACR Torq-Set driver bit deflection failures.

The top of the head (lower photograph) clearly shows the tearing or smearing

31

of the removal wall of the recess.

Figure 29 shows a typical .250 inch diameter ACR Torq-Set driver bit

failure.

Figure 30 shows a typical modified 50 Torx fastener, driver bit, and

recess after testing.

I

32I

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- I

SECTION VII

COST ANALYSIS

The most important ingredient for a cost analysis is accurate and ade-

quate input data. At the request of the Aeronautical Systems Division, the

Defense Logistics Agency (ULA) through the Defense Industrial Supply Center

(DISC) solicited quantity price quotes from licensed and authorized sources

of Torq-Set and ACR Torq-Set fasteners. Likewise, the General Services

Administration (GSA) solicited cost quotations from licensed and authorized

sources of Torq-Set and ACR Torq-Set driver bits. Seven fastener manufac-

turers responded with price quotations. Six cost quotations were from manu-

facturers licensed to produce both the standard and ACR Torq-Set recess

fasteners. All six manufacturers indicated no difference in price between

the fasteners with either recess. The seventh respondent quoted 10% higher

price for all sizes/diameters of the ACR Torq-Set recess fasteners than the

standard Torq-Set recess fasteners.

Initially only Apex Machine and Tool Company responded with a price

quotation for the driver bits, quoting the ACR Torq-Set driver bits costing

80% more than the Torq-Set driver bits. Subsequently, a price quotation

from Zephyr Manufacturing Company indicated that the new ACR Torq-Set driver

bits would cost approximately 25% more than the Torq-Set driver bits for all

sizes. A more recent up-to-date cost quote received from Apex Machine and

Tool Company revised their original quote, indicatir.g that the cost of the

ACR Torq-Set driver bits is approximately 55% higher than the cost of com-

parable standard Torq-Set driver bits, reflecting a downward trend. In a

competitive atmosphere and for large production quantities the cost advan-

tage of the standard Torq-Set driver bits can be expected to diminish even

53

further.

Additional cost associated with any new item introduced into the DOD

inventory are the one time introduction cost (cataloging and stock number

assignment) and annual item management cost (inventory control) estimated at

$1200 and $150 respectively, in FY 80 dollars. The source of these costs

was AFLCP 173-10 dated 28 August 1980.

Any potential cost increases associated with adopting the ACR fasteners

consists of the purchase price differential, if any, between the ACR and

standard Torq-Set recess fasteners and driver bits, plus the aforementioned

cost associated with the introduction of a new item.

Potential cost reduction associated with adoption of the ACR Torq-Set

fasteners results from a decrease in damaged fasteners and the corresponding

lower drillout rate of damaged fasteners. The greater removal torque capa-

city will result in a reduced number of camouts/damaged fasteners/drillouts.

Since fastener drillouLs have an impact on manpower, aircraft downtime for

maintenance, and readiness these factors .4ould be favorably affected by

adopting the ACR feature.

The data most closely associated with camout/drillout is accumulated

under "How malfunction code" (HMC)-105 in the AFM 66-1 maintenance data

collection system. This codE encompasses "loose or damagt'i Ijolts, nuts,

screws, rivets, and fasteners, clamps, or other common hardware." This data

was analyzed, but it was found that the category was much too general to

gather any useful information concerning fastener drillout rates or manhours

associated with fastener drillouts. The lack of this data therefore preclu-

des a quantitative measure tn support a potential cost savings from a main-

tainability standpoint.

54

SECTION VIII

SERVICE EXPERIENCE

Several major airlines have gained some service experience with the

application of the ACR feature -n a variety of conical type recess fasten-

ers. In order to draw on their experience a questionnaire was sent to the

following airlines, four of which responded:

Pan American World Airways

United Airlines

American Airlines

TWA

Delta Airlines

TWA has standardized on the ACR recess fastener and is using the NAS7OIO

series screws. They procure both standard and ACR driver bits. TWA nas

insufficient experience at this time to assess the advantages/disadvantages

of the ACR recess fasteners for the service life of their aircraft. They do

not monitor the frequency of camouts or drillouts of either th- standard or

ACR recess fasteners, nor are they able to correlate bit wear/breakage with

type of recess although they report less bit wear.

Delta Airlines is using the "Deep 4" Tri-Wing #10-32 1000 countersunk

bolts with the ACR feature in three lengths on access panels. The No. 4

Tri-Wing driver bits have the ACR feature, but all other bits are standard.

A service test conducted by Delta Airlines comparing #10-32 No. 5 standard

Tri-Wing recess fasteners to the #10-32 "Deep 4" Tri-Wing ACR recess faste-

ners showed a marked decrease in camouts with the latter recess. During

this service test, no drillouts of ACR fasteners were reported yet the main-

ttenance department continued to report a high drillout rate for the

55

-t'I

, ".. . =•-i .. i".. ...... - i: n.

remaining Tri-Wing fastener system. Delta does not consider driver wear/

breakage a problem and has been unable to correlate driver wear/breakage

with a particular type of recess. Their ACR fasteners replaced NAS4403-2,

-3, and -4 fasteners commonly used for access panels. They have been ham-

pered in their expansion of the use of the ACR Tri-Wing fastener system by

the lack of NAS specifications. Delta is presently considering the NASI100

Phillips system of which some recesses have the ACR feature. Delta does not

consider fastener problems a factor in down-time scheduling.

United Airlines does not foresee the need for the ACR fasteners unless

the fasteners present an economic advantage. On the basis of their obser-

vations to date, United is of the opinion that the ribs would not survive.

On the basis of information available to United Airlines from other users,

they estimate the non-ACR driver bits to have approximately twice the life.

American Airlines has no current plans to make a significint move

towards the Anti-Camout Rib Recess Fastener System. Any commitment to a new

fastener system must be preceded by documented successful service

experience. American Airlines' principal concern is the ability of the ACR

driver bits and their ribs to stand up in service.

56

SECTION IX

CONCLUSIONS

Based on the results of the test program and the other analyses pre-

sented in this report, the following conclusions are presented:

a. The ACR Torq-Set driver bit/ACR Torq-Set recess fastener combination

demonstrated generally increased first and second effort removal torque

capability when compared to the standard Torq-Set driver bit,'standard

Torq-Set recess fastener combination.

b. The ACR feature in either the Torq-Set driver bit or Torq-Set

fastener recess when used with either the standard Torq-Set fdstener recess

or standard Torq-Set driver bit respectively, demonstrated comparable or

improved removal torque capability when compared to the standard Torq-Set

driver bit/ standard Torq-Set recess fastener combination.

c. The driver bits with and without the ACR feature can be used

interchangeably with either the standard or ACR !orq-Set recess fasteners.

d. No price differential exists between the standard and ACR Torq-Set

recess fasteners. The cost benefits are realized in lower drillout rate of

damaged " . .

e. The cost of the ACR Torq-Set driver bits is higher than the cost of

the standard Torq-Set driver bits. In a competitive atmosphere and for

large production quantities, the cost advantage of the standard Torq-Set

driver bits can be expected to diminish.

f. The continued coexistence of the Torq-Set recess standard, MS33781,

and the ACR Torq-Set recess standard, MS14191, will provide suitable alter-

natives whei, t;,e aircraft manufacturer selects the Torq-Set fasteners for

his design.

3 7

- a,'- J

SECTION X

RECOMMENDATIONS

On the basis of the results of this evaluation, the following recomren-

dations z ý presented:

1. The Department of Defense per-mit the use of the ACR iorq-Set fastening

system as a suitable alternate for the standard Torq-Se. fastening system.

2. The cognizant military services maintain the standardization documents,

MS14191 and MS33781, for the ACR and standard Torq-Set recesses, respec-

t ively.

58

APPENDIX

Observers of Testing, Lot Identification, Raw Data, and

Distribution List

59

OBSERVERS

Personnel from the fol lowing organizations observed and/or participated in

some portions of the test program:

ASD/EN WPAFB OH

ASD/ENO WPAFB OH

ASO/AFHE WPAFB OH

ASDO/ENF WPAFB OH

ASO/'ENFEM WPAFB OH

ASO/ENFEF WPAFR OH

.AFWALF I8T WPAFB OH

AFWAL/FIBEC WPAFR OH

AFWAL/ML SA WPAFR OH

AFLC/PTEM WPAFB OH

0 I SC/F SA Philadelphia PA

D ISC/ELA Philadelphia PA

Air Industries Corporation Garden Grove CA

Apex Machine and Tool Company flayton OH

Battelle Columhus Laboratories Columbus OH

Fairchild Republic Corporation Farmingdale NY i

Lockheed-Genroia Company Marietta GA

Phillips Screw Company Gloucester MA

0

60

_-=-_

SUMMARY OF TEST SPECIMENS

ASO Lot No. Source Part # Recess

1 Litton Fastening Sys. NAS1580A3T3 ACR

Lot No. M127699 (Per

Gage Penetration .063 MS141G1)

2 Litton Fastening Sys. NAS158OA3T5 ACR

Lot No. M127698 (Per

Gage Penetration .067 MSIlIql)

3 P.R. Fastener Corp. NAS1580A3T8 STO

Lot No. 78-3042 (per

Gage Penetration .061 MS33781)

4 Screw Corp. Div of VSI NASI58OA3T6 STO

Lot No. 47782 (per

Gage Penetration .060-.061 MS33781)

5 P.R. Fastener Corp. NAS517-3-3 STD

Lot No. G-3850 Heat 09023 (Per

Gage Penetration .066 MS33781)

6 Mid America Aerospace NAS158OA3T6 STr)

Lot No. - unknown - parts (Per

From Grumman Stores MS337SI)

Gage Denetration .r056,067

7 Mid America Aerospace NASIROA4T4 ACR

Lot No. 81-09'>A (Per

Gage Penctration .086-.08R MS14191)

61

ASD Lot No. Source Part # Recess

8 Mid America Aerospace NASI58OA4T8 STO

Lot No. Unknown - Parts (Per

From Grummwan Stores MS33781)

Gage Penetration .078-.088

9 Litton Fastening Sys. NAS154-4 STO

Lot No. M98252 (Per

Gage Penetration .084-..086 MS33781)

10 Mid America Aerospace NAS1153E3 STD

Lot No. Unknown-Parts (Per

From Grumman Stores MS33781)


1I Parts Identified only NAS1623-4 STD

by a "K" Presumably (Per

Kenaloy Co. L.ot NO,. Unknown- MS33 7 81)

Parts from WPAFB Base Supply

Gage Penetration .060,-.064

12 Screw Corp. of VSI 75344A8 STD

Lot No. Unknown (Per

Gage Penetration .054-.074 MS33781)

13 Air Industries Corp. NAS1581C4T5 STO

Lot No. Unknown-Parts (A-286) (Per

From General Dynamics MS33781)

Fort Worth Div.


62

ASD Lot No. Source Part # Recess

14 Air Industries Corp. NASI58OC3T5 STD

Lot No. Unknown-Parts kA-286) (Per

From General Dynamics, MS33781)

Fort Worth Div.

Gage Penetration -. 052-.060

15 Air Industries Corp. NAS1580C417 STD

Lot No. Unknown-Parts (A-286) (Per


Fort Worth Div.


16 Air Industries Corp. NAS1581A4T5 STD


From General Dynamics MS33781)

Fort Worth Div.

Gage Penetration, .048-.063

17 Air Industries Corp. NASI58OA4T6 STD



Fort Worth Div.


18 Air Industries Corp. NAS1580A3T5 STD


From General Dynami.s, MS33781)

Fort Worth Div.


63

______________|__ _'

ASO Lot No. Source Part # Recess

19 Air Industries Corp. 413A4-12 Torx

Lot No. - Unknown

Gage Penetration - Not measured

20 Air Industries Corp. 406A3-9 Torx

Lot No. - Unknown

Gage Penetration - Not measured

64

Driver Bits Tested

Size Configuration Mfrg. # & Lot Number

No. 10 Standard Torq-Set Bits Apex 170-10 DA-037-227

No. 10 Standard Torq-Set Bits Apex 170-10 564659

No. 10 ACR Torq-Set Bits Apex 170-10 ACR DA-038-768

1/4" Standard Torq-Set Bits Apex 170-1/4 DA-037-227

1/41 mCR Torq-Set Bits Apex 170-1/4 ACR DA-O10-6146

No. 10 Torx 30 Taper MagnaTX20W Special

No. 10 Torx 30 Taper Apex'TX20W Unknown

1/4 Torx 50 Taper MagnaTXlOW Special

1/4 Torx 50Taper ApexTX30W Unknown

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DISTRIBUTION LIST

DOD AND OTHER GOVERNMENT ORGANIZATIONS

ASD/ENFEM (Mr. R. P. Stewart) MCLIDP

WPAFB OH 45433 WPAFR OH 45433

ASO/ENESS HO AFLC/MAHIT (Mr. Larry Marler)

WPAFB OH 45433 WPAFB OH 45433

ASD/ENFS HO AFSC/ALXP (Clark Walker)

WPAFB OH 45433 Andrews AFB MD 20334

ASD/ENFZ HO AFSC/SDTA

WPAFB OH 45433 Major Frank MayoAndrews AFB MD 20334

ASD/B1EFS (Win Geese)WPAFB OH 45433 HO USAF/ROPT

Major John Delauche

ASD/AFEF (Tom Oole) Pentagon

WPAFB OH 45433 Washington D.C. 20330

ASD/TAFE (John Hutson) AUK/LSE

WPAFB OH 45433 Maxwell AFB AL 36112

ASn/YPEF (Don Russel ) WR-ALC/MMIRDA

WPAFB OH 45433 Mr. E. RoseRobins AFB GA 31093

ASD/RWEF (E. Fisert)WPAFR OH 45433 WR-ALC/MMSRBA

Mr. Jim Peale

AFWAL/MLSA (Mr. Robert Urzi) Robins AFR GA 31093WPAFB OH 45433 SM/ALC/MMSR (Bill Southerland)

AFWAL/MLSA (Neal Ontko) McClellan AFB CA 95652WAPAFB OH 45433 AF SA/ALC/MMIRCC (Art Laback)

AFWAL/FIBE ýMr. John Potter) Kelly AFB TX 7R241

WPAFB OH 45433HO MAC/LGMM

AF ALD/PTEE (Fred Dellostritto) Scott AFB IL 62225

WPAFB OH 45433HO TAC/LGMM

AFWAL/TST Langley AFR VA 23365

WPAF8 OH 45433HO SAC/LGMM

4950TW/AMDS (Marvin Lindamood) Offutt AFR NE 68113

WPAFB OH 45433USA Armament R&D Command

CASO/LODSHD ORDAR-TST-S (M. E. Taylor)

Ernr,-t Vega Dover NJ 07801

Federal CenterBattle Creek MI 49016

101

USA Aviation R&D Command NASA (Mr. Rogert 0. Hall)F IRDAV-EGO (S. G. Garrett) DD-MED-42

4300 Goodfellow Blvd, Rldg 105 Kennedy Space Center FL 32899St Louis MO 63120

NASA (Mr'. Joseph W. Montano)Naval Air Development Center Code EH23Al Simkins/Mike Zurko M&P Lab Bldg 4612Code 6013 NASA-MSFCWarminster PA 18974 Huntsville AL 35812

Naval Air Engineering Center NASA (Mr. Carl M. Wood)Mr. Chas. Milligan EH-44ESSD Code 9311 Marshall Space Flight CtrLakehurst NJ 08733 Huntsville AL 35812

Naval Air Systems Command NASA (Mr. John Aberg)Mr. Garland Norman Code FLO3AIR-53033 MSFC Specification ProgramWashington DC 20361 Marshall Space Flight Ctr

Huntsville AL 35812Navy Material CommandMr. Harry J. Dickinson NASA Goddard Space Flight CtrCode 0423 Ja.,res KerleyWashiigton DC 20361 Greenbelt MD 20771

Defense FlectroriL Supply Ctr ,OTIC/TCAMr. Ivan Jones Cameron StationDESC/EMM Alexandria VA 22314Dayton 03 45444

Defense Industrial Supply CtrDISC-ESM/James Nealon700 Robins AvePhiladelphia PA 19111

OUSD/DMSSO/PSDCol W. Larimer/W. S. FinkelTwo Skyline Place Suite 14035203 Leesburg PikeFalls Church VA 22041

Federal Aviation AdminAndy AnderjaskaFS-120800 Independence Ave SWWashington DC 2n591

General Services AdministrationATTN: W. R. Wacker, DirectorEngineering and Technical Man. niNational Supply Service (FTT)Washington DC 20406

102

_____OWN

PRIME AEROSPACE MANUFACTURERS

Aerojet-General Corp Boeing £ommercial Airplane CoMr. G. M. Waki Mr. Frank JaroszDept 8001 Bldg 170 MS 6C-06: Bldg 7-82-2P.O. Box 296 P.O. Box 3707Azusa CA 91702 Seattle WA 98124

Aerojet-General Corp Boeing Commerical Airplane CoW. E. O'Dierr/j. L. Smuts/G. A. Loomer Mr. Jim HowellP.O. Box 13400 MS 73-43Sacramento CA 95813 P.O. Box 3707

Seattle WA 98124AVC0 Aerostructures Div

Howard Judd Boeing Military Airplane CoManager, Value Analysis R. HemingwayP.O. Box 210 Orgn 3-72544, MS K76-67Nashville TN 37202 3801 S. Oliver

Wichita KS 67210AVCO SystemsMr. Russ Schneider Boeinq Vertol Co201 Lowell St Mr. ý. RatzWilmington MA 01887 Orgn 8-7010 MSP32-07

P.O. Box 16858B. F. Goodrich Co Philadelphia PA 19142B.F. Goodrich Engineered SysUpendra Patel, Mark Owen Boeing Vertol CompanyMarls and Technology Roland A. OesjardinsP.O. Box 340 Mail Stop P32-494Troy OH 45373 P.O. Box 16858

Philadelphia PA 19142Beech Aircraft CoMr. C. Wilkinson/R. Billings Canadair Ltd9709 E. Central St Mr. C. Mikelson/Ken BarronsWichita KS 67201 P.O. Box 60,7, Station "A"

Montreal, Quebec, H3C 3G9 CanadaBell Aerospace TextronR. J. DyBas Cessna Aircraft CoP.O. Box I (MZU60) B. E. PeterrnanBuffalo NY 14240 Walace Division

Wichita KS 67201Bell Helicopter TextronStandards Engineering CPAIREd Ryba/Dept 81 Mr. Kenneth Sheh, P. Eng.P.O. Box 482 Mgr. Structures EngineeringFort Worth TX 76101 One Grant McConachie Way

Vancouver International AirportBoeing Commercial Airplane Co Vancouver, S.C., V7B IVI CanadaMr. Cecil E. ParsonsMS3N-33 De Havilland Aircraft of Canada, LtdP.O. Box 3707 Mr. S. SchrattnerSeattle WA 98124 Garatt Blvd

fDownsview, Ontario, M3K 1Y5 Canada

103

Deere & Co Tech Center Hughes Helicopters3300 River Dr C. B. Sheckells/R. H. HoldenMoline IL 61265 M.S. 305 T352

Centinela and Teale StF-Systems Inc Culver City CA 90230J. L. RainboltP.O. Box 1056 Kaman Aerospace CorpGreenville TX 75401 Edward J. Nagy/R. Bassler

P.O. Box 2Electrospace Systems Inc Bloomfield CT 06002Durward E. RutledgeSystems Safety Lockheed Missiles and Space CoP.O. Box 1359 Mr. G. G. BurkeRichardson TX 75080 Orgn 62-95 Bldg 104

P.O. Box 504

Fairchild Republic Co Sunnyvale CA 94086James J. RogersMaterials Tech Specialist Lockheed-California CoMail Stop 17-M17 David G. RichardsonFarmingdale NY 11735 Dept 76-23 Bldg 63

P.O. Box 551Gates Learjet Corp Burbank CA 91520J. 0. SimonP.O. Box 7707 Lockheed-California CoWichita KA 67277 Mr. W. Zelenka/R. C. Hatton

P.O. Box 551General Dynamics Corp Dept 76-33, Bldg 80, Plt A-1Convair Div MZ 91-4710 Burbank CA 91520Mr. J. E. CliftonP.O. Box 80877 Lockheed-Georgia CompanySan Diego CA 92138 Harry S. Gibson Jr/G. Trevillion

Dept 72-72 Zone 450General Dynamics Corp Marietta GA 30063Fort Worth Div MZ-2861Engineering Specialist/Jon Allen Martin Marietta AerospaceP.O. Box 748 Michoud OperationsFort Worth Tx 76101 James F. Hart

Dept 3523Goodyear Aerospace Corp P.O. Box 29304D. W. Peterson/K. W. Gass New Orleans LA 70189Dept 693-81210 Massi'lon Rd Martin Marietta AerospaceAkron OH 44315 Orlando Aerospace

Mr. David R. KverekGrumman Aerospace Corp P.O. Box 5837Bernard H. Real Orlando FL 32855Technical Specialist FastenersMS B13-35 Martin Marietta CorpBethpage NY 11714 Wm. K. Johnson

MS T 0487Hughes Aircraft Co P.O. Box 179Mr. W. J. Quinn Denver CO 80201Bldg E-1, MSC186P.O. Box 90515El Segundo CA 90245

!04

Mcflonnell Douglas Corp Raytheon CoMcnonnell Aircraft Co Mr. J. Richardson/Mr. R. rlinjianE. L. Wall/R. E. McGraugh Woburn StDept 358 Lowell MA 01800P.O. Rox 516St Lou s MO 63166 Raytheon Co

Mr. H. BuckbeeMcDoniell Douglas Corp 528 Boston Post RdDouglas Aircraft Co Sudbury MA 01776Mr. Ni. ChenaridesDept E-28 Mail Code 35-14 Raytheon Co3855 Lakewood Blvd Mr. E. Shore/Mr. H. WuthLong Reach CA 90846 W. Main Rd

Portsmouth, RI 02871McDonnell Douglas Corp/Astronautics CoATTN: Mr Ray H. Anderson Raytheon Co5301 Bolsa Avenue Mr. S. Devellis/A. Erlich/L. MahoneyHuntington Beach CA 92646 430 Boston Post Rd

Wayland, MA 01778Menasco Manufacturing CoTexas rivision Raytheon CoMr. J. G. Randolph Missile Systems DivisionP.O. Box 7656 Jonathan Longley/R. KealeyFort Worth TX 76111 Mail Stop 00 2-20

Hartwell RdNorthrop Corp Bedford MA 0173nF-18 Uesign StandardsOrgn 3906/Zone 94 Mr. Warren Gray RCA Corporation3901 West Broadway RCA Automated Systems DivisionHawthorne CA 90250 S. P. Patrakis

P.O. Box 588 - MS 11Northrop Corporation Burlington MA 01803Joseph A. Fitzgerald/R. L. GreetanDept 3493/84 RCA CorporationOne Northrop Ave RCA Government CommunicationsHawthorne CA 90250 Systems Division

J. N. BreenNorthrop Corporation Bldg. 17A-3-1 IAdvanced System Division Camden NJ 08101MS. E631/3E Mr. Ed Stencel8900 East Washington Blvd RCA CorporationPico Rivera CA 90660 RCA/MSRD

R. E. KillionRaytheon Co Bldg 108-237Mr. J. W. Reed/Mr. F. Detour Moorestown NJ 08057 jRt 133W. Andover MA 01810 RCA Corporation

RCA Astro Electronics DivisionRaytheon Co R. Monshaw/MS 100Mr. P. Stone P.O. Box 800400 Phillip St Princeton NJ 08540Waterloo Ontario, N2J 4K6 Canada

105

Rockwell International Corp. Sikorsky Aircraft Division

Mr. Donald E. Brown Mr. G. Chesney/Mr. R. Silcox

Code GB 47 Mr. P. Sevanoff

P.O. fox 3105 North Main St

Anaheim CA 92803 Stratford CT 06602

Rockwell International Corp. Sikorsky Aircraft Division

Electronic Systems Group Mr. Glenn E. Lattin/R. Veronesi

Michael Sarni North Main St

Dept 276, GB 47 6 Stratford CT 06602

3370 Miraloma AvenueAnaheim CA 92803 Sperry CorporationMarine Systems Division

Rockwell International Corp L. .J. Kocotas

Mr. M. Pattison/C. G. Premo Charlottesville VA 22901

6633 Canoga AveCanoga Park CA 91304 Sperry Corporation

Sprry Fliqht Systems Division

Rockwell International Corp P. C. Royd

Space Systems P.O. Rox 21,111

M. Marke/K. A. Kato Phoenix AZ 85)036

12214 Lakewood BlvdDow~ney CA 90241 Sperry Div of Sperry Corp

A. C. Thompson

Rockwell International Corp MSI15

North American A/C Operations Great Neck NY 11020

Dave QuijanoP.O. Box 92098 Sundstra9d Corp

Los Angeles CA 90009 N. S. NelsonP.O. Box 7002

Rockwell International Corp Rockford IL 61125

North American A/C Operations Teledyne Ryan Aeronautical,Ted DutkoTeeyeyaAeoutc,MA-09 Mr. John J. Frisella

P.O. Box 92098 2701 Harbor Dr

Los Angeles CA 90009 San Diego CA 92112

Rockwell International Corp The '- ,ardt. Co

W. W. Duff R. M. Parks, Jr.

Dept 995-630, MC B-116 CCI Corp

P.O. Box 51308 16555 Saticoy St

Tulsa OK 74151 Van Nuys CA 91406

Rockwell Internatioral Corp The Singer Company

Columbus Division Kearfott Division

Jack E. Frost/P. Dodsworth S. Alvine, Jr.

Dept 71-521 Bldg 6 Mail Stop 12A36

4300 E. Fifth Ave Box 1259 150 Totwa Road

Columbus OH 43216 Wayne NJ 07470

Rohr Industries Inc The Singer Company

Santiago Madera Link DivisionP.O. Box 978 H. A. Jackson

Chula Vista CA 92012 Binghamton NY 13902

106

TRW IncTRW Defense and Space SystemsMr. A. G. BlackburnR5/B375One Space ParkRedondo Beach CA 90728

Vought CorporationMr. J. A. Weaver/J. H. MallettP.O. Box 225907Dallas TX 75265

Westinghouse Electric Corp

Systems Development DivJ. F. BoydP.O. Box 746Baltimore MD 21203

I

7O

1071

'NGNE MANUFACTURERS

AirResearch Rolls Royce Canada LtdMr. Ken Heist Mr. G. GordonP.O. Box 5217 PurchasingPhoenix AZ 85010 9500 Cote de Liesse Rd

Lachine, Quebec H8r 1A2 CanadaAVCO-Lycomi ngMr. Walter Witkowski Rolls Royce Ltd550 Main Street W. A. StrayStratford CT 06497 P.O. Box 31

Derby OE2 8BJ EnglandP.O. Box 894 Teledyne CAE

Indianapolis IN 46206 Mr. W. PrusaitisP.O. Box 6971

General Electric Toledo OH 43612A. Johnson/R. Hill/L. KozerskiL-Mail Drop F!85 Williams Research CorpEvandale OH 45215 Mr. A. Sciacca

Maple RdGeneral Electric Co Walled Lake MI 48042Mr. J. Skinnon/E. C. Hazelwood1000 Western AveLynn MA 01910

General ElectricMr. P. Elligott/Mr. J. Plenge100 Plastics AvePittsfield MA 01201

Hamilton Std DivisionMr. C. Fowler/Mr. J. Bagnall/Mr. N. MoreauBradley FieldWindsor Locks CT 06096

Pratt & WhitneyMr. A. B. RodeP.O. Box 10Longueil, PQCanada, J4K-4X9

Pratt & WhitneyMr. L. Jones400 Main StEast Hartford CT 06168

Pratt & Whitney Aircraft, GPDMr. Sam WebbP.O. Box 2691/ML E-1OW. Palm Beach FL 33402

108

AIRLINES

American AirlinesH. H. CunninghamMaint and Engr CenterTulsa OK 74151

Delta AirlinesMr. William Pritchard, Mr. R. StocktonDept 568Atlanta AirportAtlanta GA 30320

Pan American World AirwaysJohn L. Arcari, R. S. RodmanJohn F. Kennedy International AirportJamaica NY 11430

Trans World AirlinesMr. Lloyd MielkeKansas City Intl AirportP.O. Box 20126Kansas City MO 64195

United AirlinesBrandon MausEngineering and MaintenanceSan Francisco Intl AirportSan Francisco CA 94128

109

VENDOR/FASTENER MANUFACTURERS

Abbott-Interfast Corp Astro PunchLon Dehaitre, Vice President Mr. Peter Thierjung190 Abbot Drive 13120 Arctic CircleWheeling IL 60090 Santa Fe Springs CA 90670

Adel Fasteners Division Automatic Screw Machine Products CoTransamerica DeLaval Corp ATTN: Mr. Frank K. Horton/Chief EngrJohn Craig P.O. Box 1608P.O. Box 7727 Decatur AL. 35602Huntington WV 25778

Avdel CorporationAerofast Inc Bill Barthel, Sales ManagerJack R. Martens 50 Lackawanna Ve.P.O. Box 324 Parsippany NJ 07054360 Gundersen DriveWheaton IL 60187 Avibank Manufacturing Co

Mr. J. A. Duran, Chief EngineerAir Industries Corp 210 S. Victory RlvdATTN: Mr. Bill Devitt/E. Baumgarten Burbank Ca 9150312570 Knott StGarden Grove CA 92641 B.F. Goodrich Co

R.F. Goodrich Engineered Prod GpAlcoa George P. VoSsMr. Russell E. Mack 500 S. Main StP.O. Box 840 Akron OH 44318Lancaster PA 17604

Bitz IncAlcoa Technical Center Mr. Rick BrownEngg Prop and Design Div 5281 Research DriveMr. William J. Oewalt Huntington Beach CA 92649Alcoa Center PA 15069

Blake Rivet CoAllfast Fastening Systems Inc B. Freeburg/B. Mason15252 Don Julian Rd 17930 Crusader AveCity of Industry CA 91744 Cerritos CA 90701

Amerace Corp, Esna 0ivision Briarwood Fasteners IncGedney McCormich/Al booth Mr. David L. Renhan2330 Vauxhall Rd 9701 Owensmouth Avenue, No 8,Union NJ 07083 Chatsworth CA 91311

American Pneumatic Tool Iriles Rivet CorpR. S. Ward, Marketing Sales Manager Mr. Franklin S. Briles/J. Aurentz14710 Maple Ave 2640 Vista Pacific DrP.O. Box 2453 Oceanside CA 92054Gardena CA 90248

Bristol Industries

Apex Machine and Tool Co Joe A. GarciaJohn George/Paul Glaser P.O. Box 630 I1025 S. Patterson Blvd 630 E. Lambert RdDayton OH 45402 Brea CA 92621

Ii0 I

•110

,____ _ __ , _, i_ _____ _____ ___-__________

Camcar Screw and Manufacturing Creer Fastener CorpMr. Robert Sellin Robert J. Greer600 18th Ave 2663 Gravel StRockford !L 61108 Fort Worth TX 76118

Camloc-Rexnord Inc Groov-Pin CorporationSpecialty Fastener Div Mr. V. J. ManobiancoWarren C. gross, Asst Engr Manager, 1125 Hendricks Causeway601 Rt 46 West Ridgefield NJ 07657HasbroUck Hgts NJ 07604

GTE SylvaniaCummaro Enterprises Mr. V. Andrews, Mr. M. Kirker,Mr. Louis A. Curimnro Mr. G. Irish6321 Gloria Prive qq A StHuntington Beach CA 92647 Needham MA 02192

fleutsch Fastener Corp H. Fred Gonnermin, )r.Mr. Larry Salter 1435 G. St. NW1315 E. Grand Ave Washington DC 20005El Segundo CA 90245

Hamant Tool Co IncFDeutsch Fastener Corp ATTN: Mr. Doug WilliamsMr. George Molina 475 Progress Rd1315 E. Grand Ave Fayton ()H 45449El Segundo CA 90245

HCH Corporation

Presspr Ind John B. Oree-rrell 11Mr. Don Larson, Torque Products Div P.O. Box 9473201 N. Worlf Rd 3625 Amblewood ,)rFranklin Park IL 60131 Florissant MO 63033

Dzus Fastener Co Inc Heli-Coil ProductsGeorge Davis, Director of Marketing Mr. John Rabuse, Manager Technical425 Union Blvd Shelter Rock LaneWest Islip NY 11795 Danbury CT 06810

E/M Lubricants Inc Hi-Shear CorporationKeith Behrens Michael M. Schuster, Dir of TechP.O. Box 2200 Adm, Patents, Mft Engrs, and AsstHighway 52 NW to Pres.,/Ed Hatter, Chief EngrWest Lafayette IN 47906 2600 Skypark Dr

Torrance CA 90509Fatigue Technology IncRob Champoux Huck Mfg CoProgram Manager Bill Busch, Manager,150 Andover Park W Technical ServicesSeattle WA 98188 P.O. Box 5268

Carson CA 90749First AmericanCharles Boda Industrial Retaining Ring Co721 East Compton Blvd Vincent A. Stabile, Pres.Compton CA 90220 57 Curdier St

Irvinton NJ 07111

Iii

Ingersoll-Rand Co Lyn-TRelot

Wiil Thon's, Proto Tool rliv Al Redlitz

615 S. State College Blvd 3150 'lanon Way

Fullerton CA 92631 Burbank CA .11505

ITW/Licensee Djivision Magna Division

Ralph W. Gilliland Vermont American Corporation

%raice Pre., Fastnerd Mr. 'im Wishart

Vice Pres., Fastener 1001 West Park Road

8501 West Higgins Rd Flizabethtown KY 42701

Chicago IL 60631

Mercury Aerospace Fasteners

J. (. King Inc Carlson Chun, Metallurgist

J. 7 . King, Jr. Box 9759711 Trabert AE3 11800 Sherman Way

Atlanta GA 30318 North Hollywood CA 91601

Kal-Gard Coating and Mfg. Co Microdot

Tom Lamona Glen Money

16616 Scnoenborn St P.l. e ox 317

Sepulveda CA 91?43 Ocean Gate NJ 02740

Kaynar Mfg. Co Inc Mid-America Aerospace

Mr. Paul Pagel, Project Engineer jim aeroePaceBoOq S. State College Blrd Mr. Jim Farrell/Ken Patrick

16201 W. 110th St

Fullerton CA 92631 Lenexa KS 66219

Kenaloy Products Monogram Aerospace Fasteners

Aerospacp Fastener Div Mr. John Pratt. Encr. Manager,

Bruce Reid/John Sherman Metal Products Gp

15500 Cornet Ave 3423 S. Garfield Ave

Santa Fe Springs CA 90670 Los Angeles CA 90040

Litton Fastening Systems Moore Tool Co

Jack Rath, Dir of Engr ATTN: Mr. Cliff Moore

3969 Paramount Blvd 21619 SW Tualatin Valley Hwy

Lakewood CA 90712 Beaverton OR 97006

Loctite Corp nNationil Utilities Corp

Girard Haviland Robert Lingscheid7059 N. Mountain Rd 135 E. Railroad Ave

Newington CT 06111 Monrovia CA 91016

Long-Lok Fasteners Olympic Fastening Systems Inc

Rockwood Systems Fraik Smode

James L. Bowman 11445 S. Dolan St614 East Main St Downey CAn 9 S241

Lancaster TX 75146

Long-Lok Fasteners Corp Orange Precision Parts

10630 Chester Rd. ATTN: Mr. Ed Clark

Cincinnati OH 45215 17930 Crusader Avenue

Cerritos CA 90701

112

Panelock Corp Rotary Components IncMr. G. M. Williams, Jr. flicronite f)ri-Lube Div142 Brickyard Rd Donald R. LewisFarmington CT 06032 816 E. Edna P1

Covina CA 91723PR FastenersMr. Vern Benson/Ed Mares Sanders Associ atesP.O. Box 1157 Mr. R. James, Mr. R. Oort,1700 West 132nd St Mr. J. GraineyGardena CA 90249 95 Canal St

Nashua NH 03060Phillips Screw CoRoger Whiteside SARMAI Kondelin Rd Rohert E. Witsen-AdelmannGloucester MA 01930 26.240 Sait-Vallier-Sur Rhone

FranceProto Tool Co, ResearchATTN: Mr. .Delo K. Chun SARMA (UK)2434 E. Fender Ave A. J. Grogono, U.K. Sales ManagerFullerton CA 92631 Green Lane Hounslow

Middlesex, EnglandPumphrey Associates IncJ. i. Punphrey, Pres. ScrewcorpP.'). Rox 3133 Mr. Al Hun, Mr. Max ThomasMarietta GA 300O'.1 13001 E. Temple Ave

City of Industry CA 91746Ramsey CorporationRoger Berkhigler Shur-Lock CorporationP.O. Box 513 Al Worthing, Manager EngrSt. Louis MO 63166 P.O. Box 19584

2541 White RdRaymond Engr. Inc. Irvine CA 9271.3Power-Dyne DivisionMr. John Bickford Simmonds Precision217 Smith St Mr. S. Walters, Mr. P. AllainMiddletown CT 06457 Panton Rd

Vergennes VT 05491Rexnord/Caml oc/Tri dai rSpecialty Fastener Grp Simmons Fastener CorporationFrank J. Cosenza, VP Engr. Gerard M. Blaney, Dir of Marketing3000 W. Lomita Blvd P.O. Box 1985Torrance, CA 905n5 Altany NY 12201

Rico Machine Snap-On Tools CorpMr. R. Barton Gene Olson, Dir., Product Res.360 Metacom Ave 2801 BOth StBristol RI 02809 Kenosha WI 631'0

Rosan Inc Sonic Industries IncFranz Berghammer, VP Sales and Pete Rush, V.P./R. S. FerryForeign Operation 13210 S. Western Ave2901 W. Coast Hwy Gardena CA 90247Newport Beach CA 92663

113

Space-Lok Inc Voi-Shan Div of VSI Corp

Scott F. Wade Kenneth 0. Borg

P.O. Box 6249 Senior Product Engr

2526 N. Ontario St 8463 Higuera St

Burbank CA 91504 Culver City CA 90230

SPS Technologies Waldes-Kohindor Inc

I. A. Roach/K. Kulju/J. Benz James F. Gearing

Highland Ave General Sales Mgr

Jenkintown PA 19046 47-16 Austel PlaceLong island City NY 11101

SPS TechnologiesMr. Troyce Wiley Waldick Aerospace Devices Inc2701 S. Harbor Blvd Paul B. Lessard/PresSanta Ana CA 92702 P.O. Box 1169

Wall NJ 07719

T.A. Manufacturing CorpMr. R. M. Byerly West Coast D eroapace Inc

375 W. Arden Ave John DeanGlendale CA 9120•3 P.O. Box 393

Kenmore WA 98023

The Hartwell Corporation Western Electric

Mr. J. W. Chambers Ps. ElectrSales Manager Au A. Payleitner900 S. Richfield Rd Aurora IL 60504Placentia CA 92670

Western Sky Industries

Tiodize Co Inc Jack H. Bell/Pres

Thomas R. Adams, Pres. 21300 Cloud Way

15272 Tiodize Cir Hayward CA 94545

Huntington Beach CA 92649 Wrentham Steel Products

Townsend Textron/Cherry Fasteners Mr. 0,. Youngdahl , Mr. M. B. Hammond

Bill Causey Kendrick St

P.O. Box 2151 Wrentham MA 02093

1224 F. Warner AveSanta Ana CA 92707 Zephyr Manufacturing Co Inc

Mr. Hal Bock

United Drill Busing Corp pf.O. Box 759

Mr. Dale L. Bethke, Pres 201 Hindry Ave

1209 Woodruff Ave Inglewood CA 90307

Downey CA 92041

vaile)-Todeco IncMr. Rudolf Brard12975 Brddley AveSylmar CA 91342

Voi-Shan Div of VSI CorpAT[N: Mr. Ed WalshAxewood Bldg, East Suite 240Butler & Skippack PikeAmbler PA 19002

114

SAE- IS0/TC20/SC4-SCAGMembership List

A. Collins Lawrence J. DoyleThe Boeing Co AVRADCOM/DRDAV-EQAMail Stop 5A-02 P.O. Box 209P.O. Box 3707 Seattle WA 98124Seattle WA 98124

Manuel A. BieraE. F. Riordan Rockwell International CorpP&W Aircraft Group-CPD Dept 246-021 MS GB-75Engrg EB3 3370 Miralama Ave400 S. Main St Anaheim CA 92803East Hartford CT 06108

P. D. Myers

E. L. Thomas Kaynar Manufacturing CoAir Transport Assoc of America P.O. Box 30011709 New York Ave NW 800 S. State College BlvdWashington DC 20006 Fullerton CA 92631

Edward Adam Robert SheafferATTN: DISC-ESP SPS Technologies700 Rohbins Ave Highland AvePhiladelphia PA 19111 Jenkintown PA 29046

G. Kikendall S. N. KennedyLockheed Aircraft Corp Jet Propulsion LabDept 75-74, 80, A-i Calif. Inst. of Tech.P.O. Box 551 4800 Oak Grove DrBurbank CA 91503 Pasadena CA 91103

G. 'ý. Garcina Barbara Boykin, SecretariatDetroit Diesel Alison Aerospace Industry Assoc of AmericaDiv of GMC 1725 neSales St NWP.O. Box 894 Washington DC 20036Speed Code 1117Indianapolis IN 46204 U. Sarsanti

11 Brookhead AvenueG. W. Tyree Beverly MA 01915Lockheed California CoP.O. Box 250 W. C. FountainD/72-71, Bldg 311 Bell Helicopter/TextronBurbank CA 91500 P.O. Box 494

Fort Worth TX 76101Jose R. ElfalenBoeing Aerospace Co W. J. QuinnOrganization 2-5052, MS 8C-53 Hughes Aircraft CoP.O. Box 3999 Technology Support DivisicnSeattle WA 98124 Bldg 316, MSR129

Culver City CA 90230L. F. LeyheVoi-Shan Manufacturing Co8463 Hiquera StCulver City CA 90230

, , , • , - - •11-5• •

F

EUROPEAN MAILING LIST

Aerospatiale, Michael Guerlet-RBP 376 fDieter Strelow12 Rue Pasteur neutscher Schraubenverbaud e.v.Suresnes 72 Schadowstrasse 42Paris, France 4000 Dusseldorf 1, W. GermanyIIAerospatiale-flivision Avions Din Deutsches Institut for Normung e.v.M. DePont-Chief Stds Normensteele Luftfahrt316 Route De Bayonne Kamenkestrasse 8BP No. 3153 Gerhard H. Junker-Geschaftsfuhrer31(153 Toulouse, France D-5000 Koln 1, W. Geniiany

Blanc Aero Eric BarnesSiege Social 338 Wolverton AveMarcel Gottscheck-Marketing Dir Kingston Upon Thames15 Rue Lasson Surrey, England75012 Paris, France

Goltenbodt and Geisselhart GmbHBritish Aerospace Aircraft Gp C. GeisselhartJack Wilcock-Chief of Stds Postfach 1165Wzrton Div Zuffenhauser ,trasse 75,

Warton Aerodrome 7015 Korntal-Munchingen 1, W. GermanyPresont, Lancashire PR4 lAX England

J. F. Stoddart

British Aerospace Gp Procurement Executi,,eHawker-Siddeley Aviation Ministry of DefenceWilfred Williams - P.A. PQO/AEIChester Rd Aeronautical Quality Assurance DirBroughton Harefield, UxbridgeChester CH4 QDR, England Middlesex 1189 6B England

British Aerospace Gp, Ken Shaw, Linread LtdCh. Stds Alan Lynall-nirHawker-Siddeley Aviation P.O. Box 21Hatfield Cox StHertfordshire AL 10 9TL England Birmingham B31RP England

British Aerospace Group Linread LtdHawker-Siddeley Aviation Brian Swann-Marketing DirPeter Boid-Chief Stds Enar Aircraft Products DivKingston-Brough Div P.O. Box 28Brough Crossgate RdNorth Humberside HU 15 1 EQ England Parkfarm Industrial Estate

Redditch 898 7TD EnglandBritish Airways

Mr. Ken A. Whittle (I.A.T.A.) MBB Messerschmitt-Boklow-Blohm GmbHL3n6 TBA, S405 Peter Nickel, Gunter PetersonP.O. Box No. 10 Div of Hamburger FlugzeugbauLondon Heathrow Airport Postfach 950109Hou ns low 0) 2103 Hamburg 95 W. GermanyMiddlesex IW6 2JA England

116

Ministry of DefenceAD/Stan (Air) SAE I Rm 262St Giles Court 1Maurice GreenSt. Giles High StLondon WC2H 8LD England

Saah-Scania Aerospace CpEvald Eriksson-Sr. Str Res EngS-581 88 LinkopingSweden

SPS European Div (Unbrako-Coventry)Charles Matthews-ManagerProduct EngineeringP.O. Box 38Burnaby RdCoventry CV6 4AE England

Society of British Aerospace Co LtdJohn Radford29 King St, St JamesLondon SWIY England

T. J. Rrooks, LtdRon Parker - Tech Sales Man.191 Barkby RdLeicester LE4 7HX England

Trevor Smith34 Rue Boubonne31000 Toulouse, France

Vereingte Flugtechnisch Werke-Fokker GmbHKalman Hoffer-Chief Fatigue Anal. DeptHunfeldstrasse 1 - 5Postfach 1078452800 Bremen 1, W. Germnany

Von Moos Stahl AG, Dr. MayerKasernenplatz 1P.O. Rox 176CH-6002 Luzern, Switzerland

117

UNIVERSITIES, RESEARCH CORPSAND TEST LABORATORIES

Almay Res and Testing CorpHarry S. BrennerPresident1415 Newton StLos Aigeles CA 90021

Battelle Columbus LabsS. Ford/O. DeelSM & T Section505 King AveColumbus OH 43201

Metcut Research Assoc IncJohn B. Kohls3980 Rosslyn DrCincinnati OH 45209

Ohio State UniversityDept. of Mechanical EngineeringJack Collins206 West 18th AveColumbus CH 43210

University of West VirginiaShyam Kumar19840 Billings CtGaithersburg MD 20879

University of WisconsinDept. of Mechanical EngineeringWayne 0. MilestoneMadison WI 53706

118

TRADE ASSOCIATIONS/CONSULTANTS

Aircraft Locknut Mfgrs Assoc Jim O'BrienJohn A. Shiffert 63 Adams StExe. Oir Wilmington MA 018872017 Walnut StPhiladelphia PA 19103 John Vaughn

Technical ServicesAssembly Engineering P.O. Box 3368Hitchcock Publishing Co. Granada Hills CA 91344Robert Kellyllitchcock Building Larry SalinasWneaton IL 60187 2 Viewpoint Circle

Pomona CA 91766ASME345 E. 47th St Masco CorporationNew York NY 10017 ATTN: E. Dennis O'Connor

Corporate Patent CounselWestinghouse Electric Corp 21001 Van Born RdATTN: Mr. P.P. Zemanick Taylor M! 48180P.O. Box 10866Pittsburgh PA 15236 Mr. Dennis Wood

p.n. Box 809ASTM Bellevue WA 98009Mr. Robert D. BauerManager Mr. Douglas Hl. SecordNew Development Activities Consultant1916 Race St P.O. Box 2Philadelphia PA 19103 Marlborough CT 06447

The Distributor's Link Mr. Fred Simmons

Leo J. Coar, Editor Regency Park219 Lincoln Blvd 4147 145th Ave NEEmerson NJ 07630 Bellevue WA 98005

E. R. Friesth NASC9317 - 104th St ATTN: Mr. S.W. Siegfried, Exec SecretaryCoal Valley IL 61240 1725 DeSales St N.W.

Washington D.C. 20036Fastener Technology137 E. 36th St National Std Assoc. Inc.New York NY 10016 ATTN; Mr. Bob Toth

5161 River RdH.A.I. Washington D.C. 20016ATTN: Mr. Bill Harkinsi7 Rookledge Terrace Price B. Herndon CoDompton Plains MH 07444 10854 Metro Ct

Maryland Heights MO 63043Industrial Fasteners InstituteMr. R. B. Belford R. C. SmithTechnical Director P.O. Box 24841505 East Ohio Bldg Oxnard CA 93030Cleveland OH 44144

119

Soc of Automotive EngineersAndrew G. Salem/D. Bentley400 Commonwealth DrWarrendale PA 15096

L20

*U.S.Oovernment PrInting Offic; 1983 - 659-004/1016

ASD(ENF)-TR-83-5001 DAMAGE TOLERANCE ...RECIPIENT'S CATALOG NUMBER ASD(ENF)-TR-83-5001 G.T- CE/N6...

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Transcript of ASD(ENF)-TR-83-5001 DAMAGE TOLERANCE ...RECIPIENT'S CATALOG NUMBER ASD(ENF)-TR-83-5001 G.T- CE/N6...