March 2011 

NASA/TM-2011-217068 

NESC-RP-04-092 

 

Performance Characterization of 

Loctite® 242 and 271 

Liquid Locking Compounds (LLCs) as a 

Secondary Locking Feature for International 

Space Station (ISS) Fasteners 

Michael J. Dube 

Goddard Space Flight Center, Greenbelt, Maryland 

Wayne R. Gamwell 

Marshall Space Flight Center, Huntsville, Alabama 
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March 2011 

NASA/TM-2011-217068 

NESC-RP-04-092 

 

Performance Characterization of 

Loctite® 242 and 271 

Liquid Locking Compounds (LLCs) as a 

Secondary Locking Feature for International 

Space Station (ISS) Fasteners 

Michael J. Dube 

Goddard Space Flight Center, Greenbelt, Maryland 

Wayne R. Gamwell 

Marshall Space Flight Center, Huntsville, Alabama 
Available from: 

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7115 Standard Drive 

Hanover, MD 21076-1320 

443-757-5802 

The use of trademarks or names of manufacturers in the report is for accurate reporting and does not 

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NASA Engineering and Safety Center 

Technical Assessment Report

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Performance Characterization of Loctite® 242 and 271 Liquid 

Locking Compounds (LLCs) as a Secondary Locking Feature for 

International Space Station (ISS) Fasteners

December 2, 2010 

 
NASA Engineering and Safety Center 

Technical Assessment Report

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Report Approval and Revision History 

NOTE: This document was approved at the December 2, 2010, NRB. This document was 

submitted to the NESC Director on January 24, 2011, for configuration control. 

Approved 

Version: 

Original Signature on File 1/26/11 

1.0 NESC Director Date 

Revision Description of Revision Author Effective 

Date 

1.0 Initial Release Dr. Wayne R. Gamwell, 

Primary Author, MSFC 

Dr. Michael Dube, 

Assessment Lead, GSFC 

12/02/10 
NASA Engineering and Safety Center 

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Table of Contents 

Volume I: Technical Report 

1.0 Notification and Authorization ..................................................................................................... 6

2.0 Signature Page ................................................................................................................................ 7

3.0 Team List ........................................................................................................................................ 8

4.0 Executive Summary ....................................................................................................................... 9

5.0 Assessment Plan ........................................................................................................................... 11

6.0 Problem Description and Proposed Solutions ........................................................................... 12

7.0 Data Analysis ................................................................................................................................ 12

7.1 Establishment of Relevant Loctite® 242 and 271 Sensitivity ........................................................ 12

7.1.1 Parameters Effecting Cure (Design, Process, Environmental) ...................................................... 12

7.1.2 ISS Specific “Typical” Fastener and Process Configurations ........................................................ 14

7.1.3 Establishment of Loctite® Relevant Post-Cure Environment Considerations (Humidity, Atomic 

Oxygen, Thermal, Vibration, etc.) ................................................................................................. 15

7.1.3.1 Questions/Discussions with Henkel Loctite® ................................................................................ 16

7.2 Phase Zero Testing ......................................................................................................................... 16

7.2.1 Test Instructions ............................................................................................................................. 20

7.2.2 Test Results .................................................................................................................................... 20

7.2.3 Discussion ...................................................................................................................................... 21

7.2.4 Conclusions .................................................................................................................................... 22

7.3 Phase I Sensitivity Testing ............................................................................................................. 22

7.4 Demonstrating Loctite® 242 Cure is not a Function of Preload ..................................................... 25

7.5 Phase I(a) Zero Percent Preload Sensitivity Testing ...................................................................... 27

7.5.1 Effect of Cure Time ....................................................................................................................... 27

7.5.2 Effect of Contaminants .................................................................................................................. 28

7.5.3 Effect of Activator ......................................................................................................................... 29

7.5.4 Effect of Thread Class on Tapped Hole ......................................................................................... 30

7.5.5 Application Method Sensitivity Study ........................................................................................... 31

7.5.6 Effect of Humidity on Cure ........................................................................................................... 32

7.5.7 Overall Conclusions for Zero Percent Preload Sensitivity Testing ............................................... 33

7.6 Coefficient of Thermal Expansion (CTE) Effects of Fastener Mechanical Loading with Dissimilar 

Materials ........................................................................................................................................ 34

7.7 Phase II Environmental Testing ..................................................................................................... 35

7.7.1 NASM 1312-7 Vibration Testing .................................................................................................. 35

7.7.1.1 NASM 1312-7 Vibration Test Results ........................................................................................... 37

7.7.2 Thermal/Vacuum Soak Testing (Hot and Cold) ............................................................................ 38

7.7.2.1 Background .................................................................................................................................... 38

7.7.2.2 Results .......................................................................................................................................... 39

7.7.3 Junker Testing ................................................................................................................................ 44
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7.7.4 Thermal/Vacuum Cyclic Testing ................................................................................................... 45

7.8 Human Factors review of Application Process for LLCs in ISS Hardware................................... 47

7.9 Loctite® Application Process Comparison .................................................................................... 48

7.10 Literature Review........................................................................................................................... 48

7.11 Questions/Discussions with Henkel Loctite® ................................................................................ 48

8.0 Observations, Findings, and NESC Recommendations ........................................................... 49

8.1 Observations .................................................................................................................................. 49

8.2 Findings ......................................................................................................................................... 49

8.3 NESC Recommendations ............................................................................................................... 50

9.0 Alternate Viewpoints ................................................................................................................... 51

10.0 Other Deliverables ....................................................................................................................... 51

11.0 Lessons Learned ........................................................................................................................... 51

12.0 Definition of Terms ...................................................................................................................... 52

13.0 Acronyms List .............................................................................................................................. 53

14.0 References ..................................................................................................................................... 54

List of Figures 

Figure 7.2-1. Vibration Test Fixture ....................................................................................................... 17

Figure 7.2-2. Vibration Fixture Pin ........................................................................................................ 18

Figure 7.2-3. Vibration Fixture Spacer ................................................................................................... 18

Figure 7.2-4. Vibration Fixture Washer ................................................................................................. 19

Figure 7.2-5. Vibration Fixture, Helicoil® Test Block ........................................................................... 19

Figure 7.3-1. ANOVA on Phase I Breakloose Torque (100 percent initial torque on 

0.25 inch fasteners) ........................................................................................................... 24

Figure 7.3-2. Scatter Plot for Breakloose Torque versus Installation Torque ........................................ 25

Figure 7.5-1. Breakaway Torque versus cure time for Loctite®242 ....................................................... 28

Figure 7.5-2. Effect of Contaminants on Breakaway Torque ................................................................. 29

Figure 7.5-3. Effect of Activator use on Breakaway Torque .................................................................. 30

Figure 7.5-4. Effect of Thread Class on Breakaway Torques ................................................................ 31

Figure 7.5-5. Effect of Application Method ........................................................................................... 32

Figure 7.5-6. Effect of Humidity ............................................................................................................ 33

Figure 7.7-1. Simulated Joint ................................................................................................................. 38

Figure 7.7-2a. ANOVA on Breakloose Torque versus Exposure Time (200 °F hot case)....................... 41

Figure 7.7-2b. ANOVA on Breakaway Torque versus Exposure Time (-140 °F cold case) ................... 42

Figure 7.7-2c. ANOVA on Breakloose Torque versus Exposure Time (72 °F ambient case) ................. 42

Figure 7.7-3. ANOVA on Breakaway Torque versus Temperature ....................................................... 43

Figure 7.7-4a. Dotplot of Torque versus Test Series ................................................................................ 43

Figure 7.7-4b. Dotplot of Torque versus Exposure Temperature ............................................................. 44

Figure 7.7-5. Thermal Cycle Profile ....................................................................................................... 46

Figure 7.7-6. Test Article Removal Schedule ........................................................................................ 46
NASA Engineering and Safety Center 

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List of Tables 

Table 7.1-1 Parameters during Cure .................................................................................................... 12

Table 7.2-1. Phase Zero Vibration Test Matrix ..................................................................................... 17

Table 7.2-2. Phase Zero Vibration Test Results (A1-A15 w/ Loctite® 242; N1-N10 w/ Braycote® 601 

lubricant) ........................................................................................................................... 21

Table 7.3-1. Fastener configurations for Phase I Breakloose Torque Testing ...................................... 23

Table 7.3-2. Phase I Sensitivity Test Matrix ......................................................................................... 23

Table 7.4-1. Zero Load Wedge Fixture Test Details ............................................................................. 26

Table 7.4-2. Zero Load Wedge Fixture Test Results ............................................................................ 26

Table 7.4-3. Two-Factor ANOVA on Zero Load Wedge Fixture Test Results 

(Preload and Hole Type) ................................................................................................... 27

Table 7.4-4. Two-Factor ANOVA on Zero Load Wedge Fixture Test Results 

(Cure Environment and Hole Type) ................................................................................. 27

Table 7.7-1. NASM 1312-7 Test Matrix. .............................................................................................. 36

Table 7.7-2. NASM 1312-7 0.250-28 Vibration Testing Performance ................................................. 37

Table 7.7-3. Simulated Joint Test Matrix and Loading Conditions ...................................................... 39

Table 7.7-4. Ambient, Hot and Cold Plate Removal Times in Hours ................................................... 39

Table 7.7-5. Breakloose and Running Torque Results for Thermal Vacuum Cyclic 

Testing of Preloaded Fasteners plus Loctite® with aluminum and Stainless Steel 

Cylinders ........................................................................................................................... 47

Volume II: Appendices 

Appendix A. Space Flight Environments for ISS ................................................................................... 60

Appendix B. Question and Answer meeting with Loctite® Representative ........................................... 62

Appendix C. Evaluation of Anaerobic Locking Compounds, Tensile Testing, Torque Tension 

Testing, and Breakloose and Running Torque Testing ..................................................... 69

Appendix D. CTE Effects of Fastener Mechanical Loads ..................................................................... 81

Appendix E. NASM1312-7 Vibration Testing Test Plan ...................................................................... 82

Appendix F. Comparison of Secondary Locking Features for Threaded Inserts, July 2007 ............... 105

Appendix G. Thermal V-acuum Testing and Results ........................................................................... 147

Appendix H. Human Factors Review of Application Process for Liquid Locking Compounds 

(LLC) in ISS Hardware ................................................................................................... 173

Appendix I. Loctite® Application Process Comparison ..................................................................... 179

Appendix J. Literature Review of the Self-Locking of Threaded Fasteners ....................................... 184

 
NASA Engineering and Safety Center 

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1.0 Notification and Authorization 

The International Space Station (ISS) Program Manager requested the NASA Engineering and 

Safety Center (NESC) to help understand and quantify sensitivities of Loctite® 242 and 271 

liquid locking compounds (LLCs) being used as a secondary locking feature on ISS fasteners. 

The ISS Program wanted to determine under what conditions Loctite® 242 and 271works 

reliably. The Out of Board Summary was approved by the NESC Review Board (NRB) on 

December 14, 2004. The assessment plan was approved by the NRB on April 21, 2004. 

Mr. John McManamen was initially assigned to lead this assessment. Dr. Michael Dube 

assumed the role of assessment lead for this task with the transition of Mr. McManamen from the 

NASA Technical Fellow for Mechanical Systems to the Space Shuttle Program Chief Engineer. 

The final report was presented for approval to the NRB on December 2, 2010. 

 
NASA Engineering and Safety Center 

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2.0 Signature Page 

Submitted by: 

Team Signature Page on File - 3/7/11 

Dr. Michael J. Dube Date Dr. Wayne R. Gamwell Date 

Significant Contributors: 

Mr. John P. McManamen Date Mr. Phil B. Hall Date 

Mr. Carlton L. Foster Date Dr. Brian J. Jensen Date 

Mr. Ed G. Hemminger Date Dr. Tina L. Beard Date 

Mr. Andrew J. Hodge Date Dr. Dan Hess Date 

Ms. Amanda M. Cutright Date 

Signatories declare the findings and observations compiled in the report are factually based from 

data extracted from Program/Project documents, contractor reports, and open literature, and/or 

generated from independently conducted tests, analysis, and inspections. 
NASA Engineering and Safety Center 

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3.0 Team List 

Name Discipline Organization 

Core Team 

Michael Dube NESC Lead GSFC 

Phil Hall Initial Team Lead MSFC 

Elvin Ahl Mechanical Systems TDT LaRC 

Carlton Foster Mechanical Systems TDT MSFC 

Brian Jensen Materials TDT LaRC 

Tina Beard Human Factors TDT ARC 

Kenny Elliott Systems Integration LaRC 

Wayne Gamwell Materials Engineer MSFC 

Ed Hemminger Structural Test and Analysis GSFC 

Andrew Hodge Materials Engineer MSFC 

Carmine Mattiello Structural Dynamics GSFC 

Kara Slade Structural Dynamics LaRC 

Jim Taylor Human Factors ARC 

Amanda Cutright Aerospace Engineer LaRC 

Roy Savage MTSO Program Analyst LaRC 

Dan Hess Mechanical Engineering University of South Florida 

Consultants 

Rajib Dasgupta Materials Engineer JSC 

Al Parrish ISS Chief Engineer (former) JSC 

Chris Hansen ISS Chief Engineer (current) JSC 

Administrative Support 

Terri Derby Project Coordinator LaRC/ATK 

Linda Burgess Planning and Control Analyst LaRC/ATK 

Erin Moran Technical Writer LaRC/ATK 

 
NASA Engineering and Safety Center 

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4.0 Executive Summary 

Several International Space Station (ISS) hardware components use Loctite® (and other polymer 

based liquid locking compounds (LLCs)) as a means of meeting the secondary (redundant) 

locking feature requirement for fasteners. The primary locking method is the fastener preload, 

with the application of the Loctite® compound which when cured is intended to resist preload 

reduction. The reliability of these compounds has been questioned due to a number of failures 

during ground testing. Failures have been related to a lack of proper procedures being followed 

for Loctite® application, leading to incomplete cure. The NASA Johnson Space Center (JSC) 

engineering community implemented a policy restricting the use of Loctite® as a secondary 

locking feature especially in safety critical applications due to this perceived unreliability. 

The ISS Program Manager requested the NASA Engineering and Safety Center (NESC) to 

characterize and quantify sensitivities of Loctite® being used as a secondary locking feature. The 

ISS Program feels they have experienced acceptable reliability with Loctite® and would like to 

determine under what conditions this type of LLC will provide predictable results. 

The findings and recommendations provided in this investigation apply to the anaerobic LLCs 

Loctite® 242 and 271. No other anaerobic LLCs were evaluated for this investigation. 

The following findings were identified during this investigation: Loctite® 242 and 271 provide 

resistance to preload reduction (i.e., vibration loosening) as least as good as that provided by 

locking inserts; military and industry specifications regarding the application and use of LLCs 

are inconsistent and contradictory; proper application processes must be developed for each 

unique application using LLCs; and the primary factors that affect LLC cure include: substrate 

cleanliness; proper substrate surface activation; thread class; hole type; and LCC application to 

both the female and male substrate surfaces. 

NESC recommendations for the use of Loctite® 242 and 271 follow: these specific LLCs are 

acceptable for use as a secondary locking feature for space hardware; development of LLC 

application processes that produce sufficient cure for the substrates to which applied is required 

by hardware developers; development of procedures and tests that verify sufficient LCC cure is 

required by hardware developers ; operations process controls must prevent contamination of 

LLCs prior to, during, and after application processes; installation operations must use activators 

on inactive/less active substrates and apply activator to both female and male fastening system 

components; hardware developers must determine the torque-tension tightening behavior of 

fastening system hardware using LLCs; hardware developers should install fasteners with LLCs 

to torque levels that produce the desired preload in the joint ; apply LLCs to both the female and 

male threaded surfaces during application processes; clean and activate both female and male 

substrate surfaces prior to applying LLCs; and do not use LLCs on hardware that has dry film 

lubrication (DFL) applied to either female or male threaded surfaces. 
NASA Engineering and Safety Center 

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Adherence to these recommended actions will allow the use of LLCs as secondary locking 

features, minimize the potential for fastener preload reductions, and maximize the reliable use of 

mechanically fastened joints. 
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5.0 Assessment Plan 

An independent review of the sensitivities of Loctite® 242 and 271for use as a secondary locking 

feature for ISS and flight vehicle applications was conducted. Testing and analyses were 

performed to determine Loctite® 242 and 271 sensitivities both as independent parameters and to 

define the boundaries for combinations of these parameters that result in a reliable secondary 

locking feature. Work completed in this assessment included: 

1. Loctite® design practices 

2. LLC qualification test standards 

3. Loctite® application processes 

4. Loctite® sensitivity identification, testing, and analysis 

5. Recommended Loctite® 242 and 271 installation practices and processes 

The assessment was conducted in three phases: Zero, I, and II, which are described in detail in 

Section 7.0. 

Phase Zero 

Phase Zero was an initial quick-look effort conducted to evaluate the effects of vibration on 

fasteners with Loctite® 242 LLC and Braycote® 601 lubricant applied to the threads and 

installed to various preload levels. 

Phase I 

Phase I defined a test and analysis plan to determine Loctite® 242 and 271 sensitivity factors and 

the exposure environment for the ISS application. The parameters and influencing factors 

included environmental-related (e.g., thermal, vacuum, vibration, interactions with other 

materials), process-related (e.g., preparation, compound application, curing), and design-related 

(e.g., materials, finishes, primers, tolerances, fastener preload, joint thickness, joint stiffness, 

fastener dimensions) factors. In addition, Military Specification (MIL-S)-46163A, National 

Aerospace Standard – former military (NASM) 1312/1-9, and American Society for Testing and 

Materials (ASTM) D5363 were evaluated to determine if they appropriately reflected installation 

practices and processes. 

Phase II 

Phase II quantified Loctite® 242 and 271 sensitivities by testing and analyses. As a result, 

recommendations for installation practices and processes for improved reliability of using 

Loctite® 242 and 271 as a fastener secondary locking feature were developed. 
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6.0 Problem Description and Proposed Solutions 

ISS fastening system hardware use anaerobic LLCs as a means of meeting secondary locking 

feature requirements. During ground vibration testing, joints that had been assembled with 

LLCs failed to prevent fastener loosening (i.e., preload loss). The reliability of LLC compounds 

for use as secondary locking features was questioned due to these failures, and the Johnson 

Space Center engineering community implemented a policy restricting the use of LLCs as a 

secondary locking feature. 

Military and industry standards for LLCs are inconsistent and contradictory. An effort to 

understand and quantify the sensitivities of LLCs as secondary locking features is required. 

Robust LLC installation processes are required that provide adequate curing of the compounds 

for applications where used, and that increase the reliability for their use in intended vibration 

environments. 

7.0 Data Analysis 

7.1 Establishment of Relevant Loctite® 242 and 271 Sensitivity 

7.1.1 Parameters Effecting Cure (Design, Process, Environmental) 

There are many parameters that can have an effect on the curing of Loctite® 242 and 271. 

Primary parameters listed are those that have been identified as contributors in various product 

specifications, LLC specifications, and contractor installation standards and specifications. 

These parameters were divided into the categories of design, process, and environmental factors. 

The parameters identified are listed in Table 7.1-1. 

Table 7.1-1 Parameters during Cure 

Design Process Environmental 

Material Where applied Temperature 

Finish How applied Relative humidity 

Part fit, tolerance, gap How much applied 

Nut or insert Surface prep/cleanliness 

Blind or thru hole Shelf Life 

Part fit, tolerance, gap Activator or none 

Preload Cure rate 

Ability to disassemble 

As indicated in Loctite® 242 and 271 product literature, cure rate will depend upon the substrate 

used and temperature. The cure time to achieve 100 percent of the breakaway strength is 

increased for less active substrates (e.g., stainless steel), and a higher breakaway strength can be 

achieved at lower cure times with higher temperature. However, the maximum breakaway is not 

dependent on temperature. Activators are documented in product literature as improving the 
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cure rate when cure times are unacceptably long, or where large gaps are present between the 

LLC and the substrate. No mention is made of the effects of pressure and percent humidity on 

the cure rate. For best results, the substrate surfaces should be cleaned and allowed to dry and 

either inherently active or coated with activator. As indicated in the product literature, aqueous 

washing systems should be checked for compatibility with the LLC. As indicated in the product 

literature, for thru holes, the LLC should be applied to the bolt at the nut engagement area. For 

blind holes, the LLC should be applied to the internal threads to the bottom of the hole. For 

sealing applications, a 360-degree bead of LLC should be applied to the leading threads of the 

male part, leaving the first thread free. The LLC should be forced into the threads to fill the 

voids. For larger threads and gaps, the LLC application should be adjusted to apply a 360-degree 

bead of LLC on the female threads. No assembly preloads are specified. The LLC is stated to 

be usable if stored in the unopened container in a dry location within the temperature range of 46 

to 60 °F. Care should be taken to prevent contamination of LLC in containers from which 

product has been dispensed. The container applicator should not touch the substrate to which the 

LLC is dispensed to prevent potential contamination. 

As indicated in the Loctite® 242 and 271 product literature, stainless steel attains less than 40 

percent of the LLC full strength after 24 hours. Henkel/Loctite® USA personnel (Appendix B) 

indicated that if no activator is used on inactive metals like stainless steel, most of the LLCs will 

take significantly longer to fully cure and the timeframe is highly unpredictable. It could take 

two to three weeks for LLCs on stainless steel substrates to fully cure without an activator. Full 

cure is defined as attaining 100 percent of the specified LLC breakaway strength. 

As indicated in Loctite® 7644 and 7471 activator product literature, these activators are designed 

to promote the cure speed of Loctite® anaerobic adhesives and sealants. Activators are 

recommended for use on passive metals or inert surfaces and with large bond gaps up to 0.010 

inches. Activator can be applied by spraying, brushing, wiping, or dipping. For small gaps (less 

than 0.010 inch), the treatment of one surface may be adequate. Activators should be allowed to 

dry completely prior to LLC application. Activated surfaces are stated to be good for bonding 

for various time limits after application (e.g., 7 days for Loctite® 7471 and 30 days for 7644). 

Conditions before reapplication is also required (i.e., should be free of contamination prior to 

application). The LLC can be applied to one or both fastening system surfaces and assembled 

immediately, then the surfaces moved in relation to each other for a few seconds on assembly to 

properly distribute the LLC and for maximum strength. 

Cure time relative to obtaining specified locking torque values is addressed in MIL-S-22473E, 

“The average locking torque of the compound after 6 hours of normal curing shall not be less 

than 50 percent and after 24 hours not less than 100 percent of the minimum value specified in 

Table I, when tested as specified in 4.6.2.1.4.” Additionally, Loctite® 7644 and 7471 are 

designed to aid cure speed to meet the locking torque requirements for various substrate 

materials. 
NASA Engineering and Safety Center 

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Cure speed relative to obtaining specified breakaway and prevailing torque values is addressed in 

MIL-S-46163, “For types I, II, and III, the average breakaway and prevailing torque for steel 

shall be not less than that specified in 1.2.1 after 24 hours. Also, the breakaway and prevailing 

torque for steel shall be not less than 50 percent of that specified in 1.2.1 after 90 minutes for 

type I; 60 minutes for type II; and 15 minutes for type III. Tests shall be as specified in 

4.6.2.1.3.” Additionally, “...the primer used in conjunction with types I, II, and III compounds 

on cadmium and zinc surfaces shall be compatible to the compounds and shall show a 

breakaway and prevailing torque of not less than 50 percent of the minimum specified in 1.2.1 

after 15 minute; and not less than 100 percent of the minimum specified in 1.2.1 after 4 hours 

when tested as specified in 4.6.3.1.” In the notes in Section 6.1, that “All three types (I, II, III) 

are designed to lock thread assemblies against working loose under shock and vibration.” 

Cure time relative to obtaining specified breakaway and prevailing torque values at standard 

conditions and “speed of cure” conditions is addressed in ASTM D5363-03, “The average 

strength of each adhesive, when tested in accordance with 7.7, shall meet the requirements 

specified for the given class in Table AN. Strength at standard conditions is obtained at 69.8 ̊F - 

77 ̊F, 45-55 percent relative humidity and a cure time of 24-26 hours. And the measured 

parameter is breakaway and prevailing torque. Cure time for “speed of cure” tests varies from 

15 minutes to 6 hours and the measured parameter is prevailing torque.” This specification 

states it is not intended for engineering design purposes. 

Typical breakaway and prevailing torque performance of cured material are indicated in 

Loctite® 242 and 271 product literature, MIL-S-22473E, and MIL-S-46163. “Cured material” is 

material that has attained 100 percent of the breakaway and/or prevailing torque strength levels 

specified in the documents for the specified LLCs. While the time or speed of cure may vary 

dependent upon parameters that affect cure, the typical torque strength performance requirements 

remain unchanged. Minimum vibration loosening (i.e., preload reduction) performance 

requirements for LLCs are not indicated in the Loctite® 242 and 271 product literature, and the 

military and industry specifications. 

7.1.2 ISS Specific “Typical” Fastener and Process Configurations 

Loctite® has been used in some locations for fastened joints on ISS Integrated Cargo Carrier 

(ICC)/External Stowage Platform (ESP)-2 hardware. Applications include the: Unpressurized 

Cargo Pallet (UCP) side brackets; Passive Flight Release Attachment Mechanism (FRAM) 

Adapter Plates; ExtraVehicular Activity (EVA) Node hole handrails; H-fixture brackets; 

External Stowage Platform Attachment Device (ESPAD) Assembly; and Keel Yoke. 

Three main issues were identified by JSC engineering with the use of Loctite® on the ICC/ESP-2 

hardware: 
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NESC Assessment #: 04-092-I

1. The hardware manufacturer, European Aeronautic Defense and Space Company (EADS), 

did not identify in its build paper a specific process for use of Loctite®, nor was the 

installation step specified to be “critical.” 

a. Discussions by JSC ISS personnel with EADS indicated that while the drawings 

did not specify an installation procedure, EADS utilized an internal process 

(MA1031620) that was considered acceptable, except for the lack of application 

of an activator to the titanium inserts (see issue 2 below). EADS indicated that 

the same technician installed all of the ESP-2 hardware. This technician 

performed installations of Loctite® for a series of unique qualification tests for 

ESP-2 hardware. After observing the process used during these tests, it was 

assessed that EADS and the technician performing the test set-up were extremely 

professional and showed a high level of competence and understanding of the 

principles and processes used to develop and qualify the hardware. It was 

determined that processes used during the qualification testing were consistent in 

quality with processes used to assemble the flight hardware, and that this test 

effectively served as a “post-assembly” qualification test. 

2. The internal process used by EADS to install the Loctite® did not call for the use of an 

activator to be applied to the titanium insert prior to installation of the fastener, which is 

contrary to the recommended practice as specified by the vendor. 

3. The use of Loctite® in this application had not been specifically qualified for use as a 

secondary locking feature, either by Loctite®, by a generic Military Specification, or by 

EADS. Most prevailing torque type locknuts and lockbolts are qualified through NASM 

1312-7 Fastener Test Methods, Method 7 – Vibration, dated August 1997. However, 

locking inserts (including Heli-Coil®, key locked-in, and thin wall locked-in) and LLCs 

are not. 

Details of the preparation and application of LLCs for several ISS manufacturing vendor sites are 

provided in Section 7.9. 

7.1.3 Establishment of Loctite® Relevant Post-Cure Environment Considerations 

(Humidity, Atomic Oxygen, Thermal, Vibration, etc.) 

A variety of environments which the Loctite® would encounter at the ISS were identified and 

considered relative to Loctite® aging and degradation. The table “Space Flight Environments for 

ISS” provided in Appendix A was prepared for this exercise. Twelve environmental factors are 

listed in the first column. The source of these factors and the worst case value expected during 

use are listed in the second and third columns. Specific comments relative to the environmental 

factor are listed in the fourth column, and the NESC team’s evaluation rationales are listed in the 

fifth column. 
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The first two environmental factors involve the ambient atmosphere. While vacuum alone was 

considered a non-factor, the combination of vacuum with low or elevated temperatures or 

temperature cycling was considered to have a possible negative impact on Loctite® stability. 

Several tests were conducted to evaluate this effect on Loctite® and results are presented in 

Sections 7.7.1 through 7.7.4. 

The next eight environmental factors involve radiation or atomic oxygen. All of these 

environments were considered inconsequential and were not subjects of testing because the 

Loctite® is located between the fastener threads and thus is not directly exposed to these 

environments. 

The external contamination environmental factor was also considered inconsequential. The 

cured Loctite® materials were considered to be relatively stable with low amounts of outgassing. Therefore, the likelihood of Loctite® causing external contamination was considered to 

be low. 

The final environmental factor considered was on-orbit humidity, which of course is zero in the 

external vacuum application. This was also considered to be inconsequential because the 

Loctite® can be used immersed in water after cure according to the product information sheets. 

7.1.3.1 Questions/Discussions with Henkel Loctite®

Throughout the Loctite® assessment, the NESC team developed questions for a Henkel/Loctite®

USA Technical Representative. These technical questions addressed many different areas and 

helped increase the team’s understanding of the different Loctite® products, product application 

procedures, and usage environments. The questions were compiled and forwarded to the Henkel 

Technical Representative. The questions provided, and the unedited answers as received are 

included in Appendix B along with the Technical Representative’s contact information. 

In summary, this question and answer exchange proved to be valuable in helping the NESC team 

better understand Loctite® LLCs. It also provided clarification for numerous company procedure 

documents evaluated by the team. 

7.2 Phase Zero Testing 

Prior to the start of Phase I testing, a quick-look Phase Zero test program was conducted. The 

test program was performed to evaluate the effects of vibration on fasteners with Loctite® 242 

LLC or Braycote® 601 lubricant applied to the threads, and installed to various preload levels. 

Prior to vibration testing, torque-tension testing was performed on each sample combination, as 

described in Table 7.2-1, to determine approximate torque values to use during vibration testing. 

The torque-tension values used for vibration testing and the expected preload values are shown 

in Table 7.2-1. Vibration testing was performed using NASM 1312-7. 
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Table 7.2-1. Phase Zero Vibration Test Matrix 

Sample Fastener Insert Type Loctite® 

LLC 

Loctite® 

Activator Lubricant Torque (in-lbs) 

Preload 

(lbs) 

A1-A5 NAS1953 MS21208F1-20 242 7471 N/A 90 2,000 

A6-A10 NAS1953 MS21208F1-20 242 7471 N/A 50 1,000 

A11-A15 NAS1953 MS21208F1-20 242 7471 N/A 25 500 

N1-N5 NAS1953 MS51830-201 N/A N/A Braycote® 

601 

80 2,000 

N6-N10 NAS1953 MS51830-201 N/A N/A Braycote® 

601 

40 1,000 

 

Testing was performed using the following items and depicted in the following figures: 

• 4130 steel test fixture (Figure 7.2-1) and spacers (Figure 7.2-3) 

• Aluminum: 

o Test fixture pins (Figure 7.2-2) 

o Spacers (Figure 7.2-3) 

o Washers (Figure 7.2-4) 

o Test blocks (Figure 7.2-5) 

NAS1587A3C washers were used under the fastener head during testing. Inserts used for the 

testing were non-locking CRES, per Table 7.2-1, installed into aluminum test blocks. Three to 

five fasteners were tested at a time. The test instructions are provided in Section 7.2.1, following 

Figures 7.2-1 through 7.2-5. 

Figure 7.2-1. Vibration Test Fixture 

SHEET 1 OF 1

NOTES: 1. BREAK SHARP EDGES

 MATERIAL: 4340 STEEL

3. UNLESS SPECIFIED 125

2

 .XX = +/- .02 ANGLES:

.XXX = +/- .010 +/- .5°

DATE: 04 - 13 - 2005

2

DRAWING NO: EM10-FX-2080 REV A

MATERIAL:

UNLESS OTHERWISE SPECIFIED

MECHANICAL

METALLURGY VIBRATION FIXTURE

1.000

5.140

2.570

.328 +.005

-.002 5 X

5 X 1.067 ±.002

.500

TYP

R .50

TYP

1.000

3.32

.664 .953

TYP

R .164

TYP

-A- i .005 A

2.067

1/2-20 UNF 2B X 1.25 DP

32

4 PROVIDE A 32 MAXIMUM FINISH ON

 INSIDE OF SLOTS

4

4

4

2.070 32

.500
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Figure 7.2-2. Vibration Fixture Pin 

Figure 7.2-3. Vibration Fixture Spacer 

SHEET 1 OF 1

NOTES: 1. BREAK SHARP EDGES

 MATERIAL: 2219-T87 OR -T851 ALUM

3. UNLESS SPECIFIED 125

2

 .XX = +/- .02 ANGLES:

.XXX = +/- .010 +/- .5°

DATE: 04 - 13 - 2005

2

DRAWING NO: EM10-FX-2081 REV -

MATERIAL:

UNLESS OTHERWISE SPECIFIED

MECHANICAL

METALLURGY VIBRATION FIXTURE PIN

.123 ±.002

1.925 ±.005

2 X .032 X 45°

O .550 ±.005

O .200 ±.002 THRU s .240 O X 45v TYP

32

32

O u .322 .002

SHEET 1 OF 1

NOTES:

1. BREAK SHARP EDGES

 MATERIAL: 2219-T87 OR -T851 ALUM

3. UNLESS SPECIFIED 125

2

 .XX = +/- .02 ANGLES:

.XXX = +/- .010 +/- .5°

DATE: 04 - 14 - 2005

2

DRAWING NO: EM10-FX-2083 REV -

MATERIAL:

UNLESS OTHERWISE SPECIFIED

MECHANICAL

METALLURGY

VIBRATION FIXTURE SPACER

O .550 ±.005 O .325 +.003

-.000 THRU

s .365 O X 45v TYP

.455 ±.001

32 32
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Figure 7.2-4. Vibration Fixture Washer 

Figure 7.2-5. Vibration Fixture, Helicoil® Test Block 

SHEET 1 OF 1

NOTES: 1. BREAK SHARP EDGES

 MATERIAL: 2219-T87 OR -T851 ALUM

3. UNLESS SPECIFIED 125

2

 .XX = +/- .02 ANGLES:

.XXX = +/- .010 +/- .5°

DATE: 04 - 13 - 2005

2

DRAWING NO: EM10-FX-2082 REV -

MATERIAL:

UNLESS OTHERWISE SPECIFIED

MECHANICAL

METALLURGY VIBRATION FIXTURE WASHER

2 X .032 X 45°

O .550 ±.005 O .200 ±.002 THRU s .220 O X 45v TYP

32 32

.123 ±.002

SHEET 1 OF 1

NOTES: 1. BREAK SHARP EDGES

 MATERIAL: 2219-T87 OR -T851

3. UNLESS SPECIFIED 125

2

 .XX = +/- .01 ANGLES:

.XXX = +/- .005 +/- .5°

DATE: 04 - 18 - 2005

2

DRAWING NO: EM10-FX-2084 REV -

MATERIAL:

UNLESS OTHERWISE SPECIFIED

MECHANICAL

METALLURGY

VIBRATION FIXTURE

HELICOIL TEST BLOCK

.750

.750

INSERT MS21208F1-20

INSTALL PER MS33646

DO NOT BREAK THRU

.750
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7.2.1 Test Instructions 

1. Test in the sequence specified in Table 7.2-1 (e.g., start with the A1-A5 inserts). 

2. Assemble fasteners into test fixture in series. (BOLTS AND INSERTS CLEANED? 

WASHERS AS-RECEIVED?) 

3. Apply Loctite® 7471 activator to fastener and insert threads. Let dry for 15 minutes 

minimum. 

4. Apply Loctite® 242 LLC to fastener and insert threads using a swab. Record Loctite®

242 expiration information. 

5. Torque each fastener/insert to the value specified in Table 7.2-1. Record the torque 

values. Record the date and time that the Loctite® 242 was applied and the fastener 

torqued. Record torque wrench/transducer calibration information. 

6. Mark the insert block/washer interfaces with a permanent scribe mark. Take a typical 

photograph. 

7. Let the Loctite® 242 cure for 30 ± 2 hours prior to testing. 

8. Photograph the test set up. 

9. Assemble the vibration test fixture onto the test machine. 

10. Test per NASM 1312-7 Vibration Test Procedures for 8 minutes duration. 

(LUBRICATED SPOOLS?) Record the date and time of testing. Stop the test if it is 

apparent that the fasteners are loosening (losing preload). 

11. Videotape the testing. 

12. Record all test anomalies post test. 

7.2.2 Test Results 

Test results are shown in Table 7.2-2. 
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Table 7.2-2. Phase Zero Vibration Test Results (A1-A15 w/ Loctite® 242; N1-N10 w/ Braycote® 601 

lubricant) 

7.2.3 Discussion 

Samples A1-A5 were installed with Loctite® 242 and torqued to 90 in-lbs representing a preload 

of approximately 2,000 pounds. During sample A1-A5 testing, the aluminum spacer galled and 

eventually froze in the steel test fixture. While none of the fasteners loosened during vibration 

testing, these tests were deemed invalid due to the spacer degradation. NASM 1312-7 specifies 

hardened steel for the fixture, pins, and spacers. The aluminum spacers were replaced with 4130 

steel spacers for the subsequent tests. 

Samples A6-A8 were installed with Loctite® 242 and torqued to 50 in-lbs representing a preload 

of approximately 1,000 pounds. The samples A6-A8 completed vibration testing without any 

relative movement of the scribe marks between the insert block/interfaces. No discernable 

movement of the scribe marks is considered acceptable performance of the configuration. 

Breakloose torques ranged from 30 to 52 percent of the installation torque values. 

Samples A11-A13 were installed with Loctite® 242 and torqued to 25 in-lbs representing a 

preload of approximately 500 pounds. For sample A11, rotation was indicated by inspection of 
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the scribe marks after testing. The breakloose torque was 13 percent of the installation torque 

value. Samples A12 and A13 failed the test by completely loosening and coming out of the test 

fixture. 

Samples N1-N4 were installed with Braycote® 601 grease and torqued to 80 in-lbs representing a 

preload of approximately 2,000 pounds. The samples N1-N4 survived vibration testing, without 

any relative movement indicated by the scribe marks between the insert block/interfaces. 

Breakloose torques ranged from 54 to 78 percent of the installation torque values. 

Samples N6-N10 were installed with Braycote® 601 lubricant and torqued to 40 in-lbs 

representing a preload of approximately 1,000 pounds. The samples N6-N10 failed vibration 

testing. Failures occurred within 45 seconds of the start of the test when the fasteners came out 

of the steel test fixture. 

7.2.4 Conclusions 

Vibration loosening is more effectively resisted by higher preloads (the primary locking feature). 

Comparing the A6-A8 and N6-N10 samples (both preloaded to approximately 1,000 lbs), 

Loctite® 242 prevented vibration loosening at this preload. Loctite® 242 was ineffective in 

providing loosening resistance for samples A11-A13 with the lowest preload of approximately 

500 pounds. 

7.3 Phase I Sensitivity Testing 

Fourteen configurations were tested in an attempt to ascertain the sensitivity of Loctite® 242 and 

271 breakloose torque strength to various factors. The factors examined included fastener 

diameter (0.164, 0.25, and 0.50 inch), female fastener configuration (non-locking Heli-coil® 

insert, H2 tapped hole, and H4 tapped hole), hole type (blind and thru hole), activator (Loctite® 

7471 and none), cleaning (Methyl-Ethyl-Ketone (MEK) and none), LLC (Loctite®242 and 271), 

and fastener torque level (25, 50, 75, and 100 percent of the fasteners yield strength). Note that 

H2 has 0.0010 inch tap cut over basic, whereas H4 has 0.0020 inches over basic. The test 

parameters and procedure are described in Appendix C. The male and female fastener 

configuration details are provided in Table 7.3-1. 
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Table 7.3-1. Fastener configurations for Phase I Breakloose Torque Testing 

Size (in) Type Class Material Finish

.1640-32 NAS 1352N-08-X UNRC-3A CRES A286 Passivated

.2500-28 NAS 1004-X UNJF-3A CRES A286 Passivated

.5000-20 NAS 1008-X UNJF-3A CRES A286 Passivated

Type Thread class Material Finish

.1640-32 Non-locking helicoil MS 122119 Coarse 1.5D CRES 300 in AL plate Passivated

.2500-28 Non-locking helicoil MS 124696 UNJF 1.5D CRES 300 in AL plate Passivated

.5000-20 Non-locking helicoil MS 124700 UNJF 1.5D CRES 300 in AL plate Passivated

Male Fastener

Female Fastener

Testing was performed on plates with an array of four by eleven holes. Fasteners were installed 

in each row at 25, 50, 75, and 100 percent of Johnson’s two-thirds yield load values (refer to 

NASM1312-8 for Johnson’s two thirds approximate method for determination of yield strength 

in fasteners). The first hole in each row was instrumented with a load cell to measure bolt 

preload. Eight fasteners in each row were installed with Loctite® LLC. The remaining three 

fasteners were installed with Braycote® 601 lubricant as a control. The test matrix for the Phase 

I sensitivity testing is shown in Table 7.3-2. Items in bold are replicates of the same baseline 

conditions. 

Table 7.3-2. Phase I Sensitivity Test Matrix 

Test Plate ID Male Fastener Female thread Hole Bolt cleaning Activator type Loctite type

16TP-1 0.164 Non-locking helicoil thru Isopropyl T-7471 242

25TP-1 0.25 Non-locking helicoil thru Isopropyl T-7471 242

25TP-2 0.25 Non-locking helicoil blind Isopropyl T-7471 242

25TP-3 0.25 H2 tap in A286 thru Isopropyl T-7471 242

25TP-4 0.25 H4 tap in A286 thru Isopropyl T-7471 242

25TP-5 0.25 H4 tap in A286 blind Isopropyl T-7471 242

25TP-7 0.25 Non-locking helicoil thru Isopropyl T-7471 242

25TP-8 0.25 Non-locking helicoil thru Isopropyl T-7471 242

25TP-7a 0.25 Non-locking helicoil thru Isopropyl no activator 242

25TP-8a 0.25 Non-locking helicoil thru No cleaning T-7471 242

25TP-9 0.25 Non-locking helicoil thru Isopropyl T-7471 242

25TP-10 0.25 Non-locking helicoil thru Isopropyl T-7471 242

50TP-1 0.5 Non-locking helicoil thru Isopropyl T-7471 271

50TP-2 0.5 H4 tap in A286 blind Isopropyl T-7471 271

An unknown event adversely affected the torque values of test plate 25TP-9 as the breakloose 

torque values were found to be much lower than those of the four other test plates with the same 

configurations. Thus, Test Plate 25TP-9 was excluded from analysis. 
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Analysis of variance (ANOVA) is a statistical test of whether or not the means of several groups 

are all equal and is useful when comparing three or more means1. ANOVA of breakloose torque 

values for the fasteners installed at 100 percent of Johnson’s two-thirds yield suggested that none 

of the test factors affected breakloose torque (see Figure 7.3-1). ANOVA on the lower 

installation torque values indicated the plates did differ (for raw data and ANOVA analyses for 

Section 7 not in this document see URL: http://www.nasa.gov/offices/nesc/home/index.html). 

However, when panels with the same configuration are compared (25TP-1, 7, 8, and 10), the 

breakloose torque values still differ for the plates. This seeming paradox can be resolved when a 

comparison between installation torque and breakloose torque is made (Figure 7.3-2). 

Installation torque is the overwhelming factor affecting breakloose torque. It became apparent 

that if an analysis of sensitivities affecting Loctite® LLC cure and subsequent breakloose 

strength is to be made, then the effect of initial torque should be eliminated. Thus, it was 

decided to repeat sensitivity testing with initial torque values of zero. This testing is discussed in 

Section 7.5. 

It should be noted that the breakloose torque values for this phase were on fasteners that had not 

experienced vibration or cyclic loading. This may explain the lack of variation between bolts 

installed with Braycote® 601 lubricant and Loctite® LLC. 

Figure 7.3-1. ANOVA on Phase I Breakloose Torque (100 percent initial torque on 0.25 inch 

fasteners) 

 

1 For more information on the ANOVA method of analysis refer to Montgomery, Douglass C., Design and Analysis of 

Experiments, 4th Edition, John Wiley and Sons, (1997) pp. 63-117.

Analysis of Variance for 100 percent Torque tightening 

Source DF SS MS F P

Test Plates 9 9502 1056 1.82 0.084

Error 60 34901 582

Total 69 44404

Individual 95% CIs For Mean

Based on Pooled StDev

Panel N Mean StDev ----------+---------+---------+------

25TP-1 8 253.75 39.45 (--------*-------) 

25TP-2 8 228.34 26.08 (-------*--------) 

25TP-3 8 250.59 11.22 (-------*--------) 

25TP-4 8 244.15 24.57 (-------*--------) 

25TP-5 7 218.72 19.96 (--------*--------) 

25TP-7 7 238.67 24.17 (--------*--------) 

25TP-7a 7 248.25 22.24 (--------*--------) 

25TP-8 6 223.97 24.65 (---------*---------) 

25TP-8a 5 242.19 20.63 (----------*----------) 

25TP-10 6 228.04 10.37 (---------*---------) 

----------+---------+---------+------

Pooled StDev = 24.12 220 240 260
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Figure 7.3-2. Scatter Plot for Breakloose Torque versus Installation Torque 

7.4 Demonstrating Loctite® 242 Cure is not a Function of Preload 

A test series was run to determine if preload affects the cure of Loctite® LLC. A test fixture (i.e., 

specifically the zero load wedge fixture) was fabricated that was capable of releasing the preload 

on a fastener after torque was applied to the fastener. Loctite® 242 was applied to the fasteners, 

the NAS1004-8A CRES A286 0.250-28 fasteners were then torqued to 50 in-lbs, and the 

Loctite® 242 was allowed to cure for 48 hours. After the Loctite® 242 cure, the preload was 

removed and the breakaway strength of the fasteners was tested. Maximum breakaway torque 

and running torque were recorded. The parameters of the experiment are provided in Table 7.4-

1. 

0

50

100

150

200

250

300

350

0 50 100 150 200 250 300 350

Initial Torque (in-lbs)

Breakloose Torque (in-lbs)

Loctite 242

Braycote
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Table 7.4-1. Zero Load Wedge Fixture Test Details 

LLC Loctite® 242 (ASTM D5363-03 Group 03, Class 2, Grade 1, blue) 

and (MIL-S-46163A Type II, Grade N) 

Activator Loctite® 7471 (Grade T) 

Fastener NAS1004-8A CRES A286 0.250-28 

Insert NASM 124696 CRES Heli-Coil® Fine Thread 1.5 Diameter 

Cure time 48 hours 

The test was repeated to assess several factors including: initial preload level (50 and 0 in-lbs), 

cure environment (ambient atmosphere and rough vacuum – 28 in Hg), and hole type (blind and 

thru hole). The test conditions and breakaway strength results are shown in Table 7.4-2. It is 

shown by Two-factor ANOVA comparing initial preload and hole type that preload has no effect 

on breakaway strength. Further testing compared cure environment and hole type. In both cases, 

the hole type affected breakaway strength. Loctite® 242 cured for 48 hours in vacuum had an 

increased breakaway torque compared to Loctite® 242 cured in ambient atmosphere. Tables 7.4-

3 and 7.4-4 show the ANOVA performed on the zero load wedge fixture test results. In the 

ANOVA, F values greater than the Fcrit values indicate statistically significant results for the 

parameters evaluated. 

Table 7.4-2. Zero Load Wedge Fixture Test Results 

Sample ID Applied Torque 

(in-lbs)

Preload (lbs) Breakloose 

Torque (in-lbs)

Hole Type

ZL-C-25-1 49.36 958 7.2 Blind

ZL-C-25-2 49.75 1033 4.1 Blind

ZL-C-25-3 50.28 1188 6.8 Blind

ZL-C-25-4 50.13 869 15.4 Thru

ZL-C-25-5 49.44 833 20.4 Thru

ZL-C-25-6 50.01 1038 13.4 Thru

ZL-C-25-10V 49.51 830 21.3 Thru

ZL-C-25-11V 49.61 1234 29.5 Thru

ZL-C-25-12V 50.05 1172 19.6 Thru

ZL-C-25-13V 50.28 968 11.2 Blind

ZL-C-25-14V 49.25 901 5.7 Blind

ZL-C-25-15V 49.52 1196 11.8 Blind

ZL-C-25-16H 13.7 Thru

ZL-C-25-17H 18.8 Thru

ZL-C-25-18H 15.3 Thru

ZL-C-25-19H 6.6 Blind

ZL-C-25-20H 8.2 Blind

ZL-C-25-21H 6.5 Blind

Finger tight

Finger tight

Finger tight

Finger tight

Finger tight

Finger tight

 
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Title:

Evaluate the Performance of Loctite® as a Secondary 

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Table 7.4-3. Two-Factor ANOVA on Zero Load Wedge Fixture Test Results (Preload and Hole Type) 

Table 7.4-4. Two-Factor ANOVA on Zero Load Wedge Fixture Test Results (Cure Environment and 

Hole Type) 

7.5 Phase I(a) Zero Percent Preload Sensitivity Testing 

A series of tests was conducted to establish Loctite® 242 breakaway strength sensitivities to 

various factors that could be present during installation. Factors examined included: cure time, 

contamination, hole type, application method, use of activator, humidity, and thread class on 

tapped hole. Because the wedge fixture testing successfully demonstrated that initial preload did 

not affect breakaway strength (after the preload was relaxed), sensitivity testing was performed 

without preload using aluminum panels with stainless inserts. Fasteners were installed in panels 

with four rows of eleven holes to examine various sensitivity factors. Fasteners and inserts were 

cleaned with MEK solvent prior to installation. Fasteners were then spray coated with Loctite® 

7471 activator and allowed to dry at least 15 minutes. Loctite® 242 was applied by dropper to 

coat the fastener for thru hole installation. Loctite® 242 was applied to both fastener and insert 

for blind hole installation. 

7.5.1 Effect of Cure Time 

An initial series of tests was conducted on four panels to evaluate the effect of cure time on 

breakaway strength. No trend was observed in breakaway strength for fasteners in thru holes. 

However, the breakaway strength continued to increase to 96 hours for the blind holes (Figure 

7.5-1). This testing established a cure time of 48 hours as sufficient for testing sensitivity factors 

on thru holes. The log curves in Figure 7.5-1 are fitted curves of the mean values of the thru and 

blind hole data sets. 

Source of Variation SS df MS F P-value F crit

Blind vs thru hole 276.29 1 276.29 46.76 0.000133 5.32

50 in-lb initial torque vs no initial torque 0.26 1 0.26 0.04 0.838 5.32

Interaction 1.79 1 1.79 0.30 0.597 5.32

Within 47.27 8 5.91

Total 325.62 11

Source of Variation SS df MS F P-value F crit

Blind vs thru hole 441.90 1 441.90 31.64 0.000496 5.32

ambient vs vacuum cure 84.27 1 84.27 6.03 0.040 5.32

Interaction 9.36 1 9.36 0.67 0.437 5.32

Within 111.75 8 13.97

Total 647.27 11
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Figure 7.5-1. Breakaway Torque versus cure time for Loctite® 242 

7.5.2 Effect of Contaminants 

An attempt was made to determine how Loctite® 242 would adhere to DFL bolts. DFL bolts 

were installed and cured in the same manner as previous testing. Similarly, a second panel was 

used to evaluate the effect of Braycote® 601 lubricant contamination. Braycote® 601 was 

applied to inserts and subsequently cleaned off. Cleaning was performed by scrubbing the 

inserts with a test tube brush that had been immersed in MEK. Other contamination factors 

examined included using as-received fasteners and recycled inserts that contained residual 

Loctite® 242 from previous installations. No difference in breakaway strength is evident by 

ANOVA when inserts contaminated with Loctite® 242 are reused. A small difference was 

detected when the as-received fastener was used without cleaning. The greatest observed 

reduction in strengths was from contamination of DFL and insufficiently cleaned Braycote® 601 

lubrication. More notable than the drop in average breakaway strength was the increase in 

variance. The contamination study results are displayed in Figure 7.5-2. 

0

5

10

15

20

25

30

35

0 10 20 30 40 50 60 70 80 90 100

Cure Time (hours)

Breakaway Torque (in-lbs) 

Thru Hole

Blind Hole

Log. (Blind Hole)

Log. (Thru Hole)
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Figure 7.5-2. Effect of Contaminants on Breakaway Torque 

7.5.3 Effect of Activator 

The effect of Loctite® 7471 Grade T activator was examined in two series of tests. An activator 

is used for anaerobic LLCs to speed the cure time. Henkel/Loctite® USA recommends the use of 

an activator in applications with passive metals. A panel was prepared without using activator 

on the fasteners and compared to the control panels. The average breakaway strength when 

activator was not used had approximately a 10 percent lower value than when activator was used 

(Figure 7.5-3). Two additional panels from the contamination study (contaminated with residual 

Loctite® 242 in the inserts) were installed with fasteners that were activated on one panel and 

fasteners that were not sprayed with activator on the other panel. Again, the average breakaway 

strength when activator was not used had approximately a 10 percent lower value than when 

activator was used (Figure 7.5-3). These effects are statistically significant in the ANOVAs. 

0

5

10

15

20

25

0 123456

Treatment

Breakaway Torque (in-lbs)

(1) TP-21 Control

(2) TP-11,12, & 13 control

(3) TP-18 Loctite contaminated inserts, 

primer used on fasteners.

(4) TP-15 Dry Film Lubricated Bolt

(5) TP-17 As recieved fastener (7471 

activator was used)

(6) TP-22 Braycote contaminated inserts 

cleaned with MEK

Groups Count Average Variance

(1) 21 14.2 8.0

(2) 84 14.6 6.1

(3) 32 13.8 8.2

(4) 32 7.9 24.3

(5) 32 13.2 4.3

(6) 38 12.3 15.7
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Figure 7.5-3. Effect of Activator use on Breakaway Torque 

7.5.4 Effect of Thread Class on Tapped Hole 

In this series of testing two A286 plates were substituted for the aluminum plates with nonlocking Heli-coil® inserts. Four rows of eleven tapped holes had either an H2 or H4 class 3 

thread tolerance. Plates and fasteners were cleaned and installed with the same method as 

before. Fasteners were installed to the same depth in all holes. Breakaway torque was measured 

after Loctite® 242 cure. The plate with H2 thread had a 14 percent greater average breakaway 

torque than the H4 thread (Figure 7.5-4). This effect is statistically significant in the ANOVA. 

0

5

10

15

20

25

012 345

Treatment

Breakaway Torque (in-lbs)

(1) TP-21 Control

(2) TP-11,12, & 13 control

(3) TP-16 No primer used on fasteners.

(4) TP-18 Loctite contaminated inserts, 

Primer used on fasteners.

(5) TP-19 Loctite contaminated inserts, No 

primer used on fasteners.

Groups Count Average Variance

(1) 21 14.2 8.0

(2) 84 14.6 6.1

(3) 32 12.4 4.9

(4) 32 13.8 8.2

(5) 32 11.9 6.3
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Figure 7.5-4. Effect of Thread Class on Breakaway Torques 

7.5.5 Application Method Sensitivity Study 

For the purpose of the sensitivity study, Loctite® 242 was applied per manufacturer’s 

recommendations as a baseline. Henkel Loctite® USA recommends in the Technical Data Sheet 

for Loctite® 242 applying the LLC to the bolt only for thru holes, and down the internal threads 

to the bottom of the hole for blind holes. However, there are varying application procedures in 

actual use (see Section 7.9). It was also observed in this study that initial test results from blind 

holes had a higher breakaway torque than the thru holes. Was this a result of differing 

configuration or application? A comparison of the application technique with blind and thru 

holes was performed in which Loctite® 242 was applied to bolt only, and both bolt and insert for 

the two hole types. One thru hole panel and one blind hole panel had Loctite® 242 applied to 

only the fastener on half of the samples. The other half of the samples had Loctite® 242 applied 

to both the fastener and the insert. The thru hole panel replicated the earlier results. The samples 

with Loctite® 242 on both insert and fastener had a strength equivalent to the first series of blind 

hole tests (both surfaces coated). The samples with Loctite® 242 on only the fasteners had 

strengths equivalent to the earlier thru hole tests (only fastener coated). However, when the 

blind hole panel was repeated with the application method as the variable, the earlier results 

could not be replicated (See series 5 versus series 1 in Figure 7.5-5). The breakaway torque 

values were lower than expected based upon previous test results. The high variance suggests an 

unknown factor affected the test results. Despite the discrepancy in the data, coating both the 

female and male threaded surfaces results in a higher breakaway torque for either hole type. 

0

5

10

15

20

25

30

35

Treatment

Breakaway Torque (in-lbs)

H2 H4
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Figure 7.5-5. Effect of Application Method 

7.5.6 Effect of Humidity on Cure 

The effect of humidity on breakaway strength of Loctite® 242 was tested in a number of ways. 

The breakaway strength was measured after standard cure times (48 hours) in humidity, 48 hour 

cure in humidity followed by 48 hour exposure to ambient atmosphere, and standard 48 hour 

ambient atmosphere cure followed by 48 hour exposure to humidity. Humidity conditioning was 

performed in a humidity chamber at 90oF with 90 percent relative humidity. The test matrix was 

performed in replicate using two different Loctite® 242 application techniques. Fasteners were 

installed with Loctite® 242 applied to the fastener threads only and Loctite® 242 applied to both 

the fastener and the insert threads. Exposure to humidity negatively affected the breakaway 

strength of samples that had Loctite® 242 applied only to the fastener threads. Humidity had no 

effect on samples that had Loctite® 242 applied to both fastener and insert threads. One 

possibility is that the Loctite® 242 provides a better seal when both surfaces are coated. 

However, further testing is required to fully understand this phenomenon. Despite the potential 

interaction observed between humidity exposure and application technique, humidity is not a 

sensitivity factor when Loctite® 242 is applied to both fastener and insert threads (Figure 7.5-6). 

0

5

10

15

20

25

30

35

012 3456

Treatment

Breakaway Torque (in-lbs)

(1) 25TP-14 Blind hole, Loctite 

applied to both fastener and 

insert threads

(2) 25TP-11, 12, & 13 Thru

hole, Loctite applied to fastener

threads only

(3) 25TP-21 Thru hole, Loctite

applied to both fastener and 

insert threads

(4) 25TP-21 Thru hole, Loctite

applied to fastener threads only

(5) 25TP-20 Blind hole, Loctite 

applied to both fastener and 

insert threads

(6) 25TP-20 Blind hole, Loctite 

applied to fastener threads only
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Figure 7.5-6. Effect of Humidity 

7.5.7 Overall Conclusions for Zero Percent Preload Sensitivity Testing 

Cure time was slower for blind holes compared to thru holes. Thru holes reached full strength in 

6 to24 hours, while blind holes continued to gain strength to 96 hours. The contamination study 

suggests that DFL bolts should not be used with Loctite® 242. When reinstalling a fastener with 

Braycote® 601 lubricant contamination present, cleaning should be performed prior to using 

Loctite® 242. Residual Loctite® 242 from a previous installation does not appear to be 

detrimental to the strength of a reinstalled fastener. Not using an activator on the stainless steel 

fastener resulted in an average decrease in breakaway strength of 10 percent. When using 

Loctite® 242 on a tapped hole, the tighter tolerance H2 hole had improved breakaway strength 

over the H4 hole. However, some of this effect may be attributable to the tighter fit. Application 

method has the greatest effect of the factors examined. Application of Loctite® 242 to both 

threaded surfaces (male and female) appears to be necessary to allow adequate coverage. Short 

term humidity exposure during and after cure has no effect on breakloose strength when Loctite®

242 has adequate coverage by application to both fastener and insert. This study finds that the 

greatest effect on breakaway strength results from contamination, poor application, and humidity 

on an inadequately coated fastener. To insure the best breakaway strength, the fastener and 

0

5

10

15

20

25

30

35

0123456789

Treatment

Breakloose Torque (ft-lbs)

(1) 48 hr ambient cure

(2) 48 hr 90F/90RH cure

(3) 96 hr 90F/90RH cure

(4) 48 hr 90F/90RH cure; 48 hr

ambient exposure

(5) 48 hr ambient cure; 48 hr

90F/90RH exposure

(6) 48 hr ambient cure

(7) 96 hr 90F/90RH cure

(8) 48 hr 90F/90RH cure; 48 hr

ambient exposure

(9) 48 hr ambient cure; 48 hr

90F/90RH exposure

Loctite applied to fastener 

threads only

Loctite applied to 

fastener and insert 

threads
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insert surfaces should be cleaned, chemically activated, and both female and male threads should 

be covered with Loctite® 242. 

7.6 Coefficient of Thermal Expansion (CTE) Effects of Fastener Mechanical 

Loading with Dissimilar Materials 

The effect of temperature change on a preloaded joint depends on CTE differences between the 

fastener and the clamped or grip material. The larger the CTE difference, the greater the 

corresponding effect on fastener preload. 

In elevated temperature extremes, an aluminum structure (grip) will expand more than a stainless 

steel fastener. This creates additional tension and preload. This situation could result in 

exceeding the fastener yield strength and/or possible damage to the threaded connection (e.g., 

thread shear tear-out). 

Similarly, in low temperature extremes, the aluminum structure (grip) will shrink more than the 

stainless steel fastener. The result is a reduction in preload and possible gapping or joint 

separation under applied loading. 

Preload alteration (gain and loss) due to temperature changes can be calculated using formula 

(10) from NASA TM-106934: 

Pth = ((KbKj)/ (Kb+Kj)) LΔT (αj-αb) 

Where: 

Pth = axial bolt load due to thermal effects, lb 

Kb = bolt stiffness, lb/in 

Kj = joint stiffness, lb/in 

L = clamped thickness, in 

ΔT = change in temperature,  ̊F 

αj = abutment coefficient of thermal expansion, in/in/ ̊F 

αb = bolt coefficient of thermal expansion, in/in/ ̊F 

The calculated effect of temperature change for the preloaded joint configuration used for 

thermal vacuum testing using various combinations of materials is provided in Appendix D. 

An example of the CTE effect calculated using the formula above is shown below. 

Based on use of 0.500-28, A286 (85 ksi) stainless steel fasteners with the following properties: 

• An effective clamping or grip length of 1.75 inch into 6061 T6 aluminum. 

• CTE = 9x10-6 in/in ̊F for A286 stainless steel and 13x10-6 in/in ̊F for 6061 T6 aluminum. 
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Assuming preload application at 70  ̊F and temperature transients between -50 and to +150  ̊F, 

the preload gain and loss was calculated using formula (10) from NASA TM-106943 as follows: 

For a cool down from 70 to -50  ̊F, the aluminum grip length of 1.75 inch would shrink 

more than stainless steel fasteners resulting in approximately 1,600 pound loss in preload. 

For heat up from 70 to +150  ̊F, the resulting preload change is approximately 1,000 

pound increase. 

If the joint is initially applied using a Johnson’s two-thirds yield preload (assuming 85 ksi yield 

fasteners), then the preload clamping force at 70  ̊F would be about 9,000 pounds for a 0.500-28 

fastener. If the estimated CTE change is applied to the predicted preload, the effective preload 

is: 

Cool-down Preload (pounds) = 9,000 – 1,600 = 7,400 

Heat-Up Preload (pounds) = 9,000 + 1,000 = 10,000 

The estimated preload variances are based on fastener and structure being at the same initial and 

final temperature. Any mismatch during the temperature transients would also affect the 

preload, but to a lesser degree. 

In summary, temperature effects must be considered when determining acceptable installation 

preloads for joints. 

7.7 Phase II Environmental Testing 

7.7.1 NASM 1312-7 Vibration Testing 

Vibration testing was conducted to evaluate the use of Loctite® 242 and 271 as a secondary 

locking feature in threaded fastening systems. Testing was conducted in accordance with 

Langley Research Center (LaRC) Test Plan LaRC-D210-01, dated February 1, 2006, except that 

the test matrix was expanded as initial test results were generated. Test Plan LaRC-D210-01 is 

included as Appendix E. Vibration testing was conducted in accordance with the NASM 1312-7. 

The NASM 1312-7 standard provides a means of qualification through accelerated vibration 

testing. The method incorporates the use of repeated or cyclic shocks to assess a fastener locking 

system. The times to failure were determined as a result of this testing. Failure was defined as 

relative angular movement of the bolt in relation to the “nut” in the fastener system. In some 

instances, the measurement of the post-test breakloose torque was also measured as a secondary 

factor. 

Four fastening systems and three fastener sizes were tested (Table 7.7-1). The fastening systems 

were: 
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1. Bolt/threaded hole 

2. Bolt/Heli-coil® insert (non-locking) 

3. Bolt/key-locking insert (non-locking) 

4. Bolt/Heli-coil® insert (locking) 

Fastener sizes tested were 0.164-32, 0.250-28, and 0.500-20. Installation torque values for 

vibration testing for the 0.500 and 0.250 inch fasteners conformed to Military Detailed 

Specification (MIL-DTL)-18240F, Detail Specification, Fastener Element, Self-Locking, 

Threaded Fastener, 250 ̊F. The torque value for the 0.164 inch fastener was derived by 

extrapolating the seating torque values in MIL-DTL-18640F. MIL-DTL-18640F defines the 

requirements for self-locking elements (such as non-metallic plug/pellet or strip features, but not 

specifically LLCs) for use in externally threaded fasteners 

Table 7.7-1. NASM 1312-7 Test Matrix. 
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Table 7.7-2. NASM 1312-7 0.250-28 Vibration Testing Performance 

Configuration 

Designation 

Number of 

Samples 

Insert Type Lubricant or 

thread locker 

Torque 

(in-lbs) 

Head Lubricant Performance 

6 54 Free running Loctite® 242 20 No head lube 10 bolts > 30k cycles 

1 142 Free running Loctite® 242 60 No head lube 77 bolts > 30k cycles 

2 41 Free running Loctite® 242 60 No head lube 23 bolts > 30k cycles 

3 43 Tapped Hole Loctite® 242 60 No head lube 13 bolts > 30k cycles 

22 33 Free running Loctite® 242 105 Braycote® head 

lube 

All bolts > 30k cycles 

9 55/11 Locking Braycote® 60/50 No head lube 12 bolts > 30k cycles 

21 33 Locking Braycote® 105 Braycote® head 

lube 

18 bolts > 30k cycles 

23 11 Locking Braycote® 115 Braycote® head 

lube 

All bolts > 30k cycles 

10 11 Locking Braycote® 176 No head lube All bolts > 30k cycles 

17 11 Free running Braycote® 84 Braycote® head 

lube 

1 bolt > 30k cycles 

15 11 Free running Braycote® 105 No head lube 7 bolts > 30k cycles 

18 11 Free running Braycote® 105 Braycote® head 

lube 

1 bolt > 30k cycles 

20 22 Free running Braycote® 105 Braycote® head 

lube 

Zero bolts > 30k cycles 

14 11 Free running Braycote® 126 No head lube 9 bolts > 30k cycles 

19 11 Free running Braycote® 126 Braycote® head 

lube 

5 bolts > 30k cycles 

11 11 Free running Braycote® 140 No head lube All bolts > 30k cycles 

7.7.1.1 NASM 1312-7 Vibration Test Results 

NASM 1312-7 vibration testing results are shown in Table 7.7-2. Performance was based on the 

number of fasteners surviving 30,000 cycles without loosening (relative angular movement) as 

indicated by marking of the fastener/substrate. Vibration testing performance results indicate the 

following: 

1. The performance of Loctite® 242 in this NASM 1312-7 vibration testing was as good as 

or better than the performance of the free running and locking inserts tested. 

2. The performance of Loctite® 242, the free running inserts, and the locking inserts 

appears to improve with increasing preload. 
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7.7.2 Thermal/Vacuum Soak Testing (Hot and Cold) 

7.7.2.1 Background 

Simulated bolted joints using Loctite® 242 were subjected to ambient (72  ̊F), hot (200  ̊F), and 

cold (-140  ̊F) soak testing in a high vacuum environment of less than 10-5 torr. Testing was 

performed to determine the breakaway torque, and running torque from 90 to 720 degrees as a 

function of time at temperature and vacuum. Samples were installed into plates populated with 

up to 25 bolts on each plate. Hot samples were heated using radiant heating to heat and maintain 

the samples at 200  ̊F. Cold samples used a cold plate to cool and maintain the sample plates to a 

temperature of -140  ̊F. Ambient samples were installed into plates at 72  ̊F. The simulated 

joint, shown in Figure 7.7-1, used NAS1004, 0.250-28 UNJF-3A fasteners to clamp a cylinder to 

an aluminum base plate. 

 

Figure 7.7-1. Simulated Joint 

Three cylinder materials, shown in Table 7.7-3, were used during the testing. Testing was 

performed using bolts inserted into non-locking Heli-coil® inserts with no preload (finger-tight) 

applied. 
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Table 7.7-3. Simulated Joint Test Matrix and Loading Conditions 

Bolt Insert Cylinder Material Initial Preload (lbs) 

NAS1004-22 MS124696 Al 6061-T6 0 

NAS1004-22 MS124696 A286 0 

NAS1004-22 MS124696 15-5 PH 0 

Thermal vacuum chambers were loaded and held at ambient, hot, or cold temperatures for 

specified periods of time. At the end of specified times, plates were removed from the chambers. 

For the hot and cold plates, the chambers were brought to ambient conditions and one plate was 

removed. The chambers were then reheated or cooled to the designated temperature and held. 

This process was performed until all the plates had been removed from the chambers. 

Table 7.7-4 shows the ambient, hot and cold plate removal times in hours from the chambers. 

Table 7.7-4. Ambient, Hot and Cold Plate Removal Times in Hours 

Plate 

Number 

Ambient (72 °F) 

Plates Removal Time 

(hrs) 

Hot (200 °F) Plates 

Removal Time (hrs) 

Cold (-140 °F) Plates 

Removal Time (hrs) 

1 48 215 263 

2 192 383 451 

3 384 479 553 

4 480 575 619 

5 576 670 715 

6 672 768 811 

7 768 862 907 

8 864 1000 1005 

9 960 1054 1099 

10 1056 1174 1197 

7.7.2.2 Results 

The breakloose torque measurements of fasteners installed with Loctite® 242 and soaked at three 

temperatures for several exposure times were analyzed. Statistical inference shows the means of 

the data groups are not equal. However, descriptive analysis of the data suggests the factors of 

exposure time and exposure temperature are likely not the cause of unequal means. Different 

sleeve materials produced no measureable difference in breakloose torques. Therefore, all rows 

of data were combined into one set regardless of sleeve material. 
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7.7.2.2.1 Inference Statistics, Exposure Time 

ANOVA was performed to test the hypothesis of equal means on two or more groups of data. 

Assumptions of the ANOVA include independence, normality, and equality of variance. The 

assumption of independence is valid in this case as any given measurement or data set should 

have no effect on another measurement (i.e., independent bolts) or data set (i.e., exposure time 

and temperature). Normality tests on each exposure time suggest the data are not normally 

distributed. Levene’s test2

 suggests variances are equal in the hot data, but unequal in the 

ambient and cold data. Although the assumptions are violated, ANOVA is often assumed robust 

against departures from normality when the sample sizes are equal. ANOVA performed on each 

temperature set suggest the means of each data set are not equal (Figures 7.7-2a and 7.7-2b). 

Sample sizes are not equal on the ambient tests. A nonparametric test3

 used when the normality 

assumption is violated, indicated medians are not equal. ANOVA is included in Figure 7.7-2c to 

display the descriptive summary statistics. 

One issue with the above inference is that it assumes the only factors evaluated within the 

temperature sets are exposure time. Since complete cure should occur before the first 

measurement in the ambient tests, these data should be considered a control group. It is apparent 

there is another factor influencing the breakloose torque within each group as all groups should 

have equal means and variances. 

7.7.2.2.2 Inference Statistics, Temperature 

If the assumption that exposure time is not a factor in the breakloose torque values and pools all 

data within each temperature group, then a comparison between temperatures can be made. It 

was determined that data are not normally distributed. A Kruskal-Wallis test concludes that the 

medians of the three temperature exposures are not equal. The ANOVA results (included for 

detailed summary statistics) are shown in Figure 7.7-3. 

7.7.2.2.3 Exploratory Data Analysis (EDA) 

EDA methods are used primarily to explore data before using more traditional methods, and are 

a useful method to visually identify unique features contained within the data. A dotplot of the 

data is useful in examining the data scatter and range. From Figure 7.7-4a it is seen that the 

variance within each group is large, in some cases the coefficient of variation is as high as 25 

percent. Figure 7.7-4a and 7.7-4b display the conclusion from the ANOVA that the means for 

the groups are not equal. 

 

2 Levene, H., “Robust Tests for the Equality of Variances”, Contributions to Probability and Statistics, ed. I. Olkin, Palo Alto, CA: Stanford 

University Press, 1960.

3 Kruskal-Wallis (ref. 2, Conover, W.J., Practical Nonparametric Statistics, 3rd Edition, John Wiley and Sons, (1999) pp. 288-

297.)
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Title:

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7.7.2.2.4 Conclusions 

A statistically significant difference means there is statistical evidence of a difference at a 

specific significance level. It does not indicate that the difference is important (or physically 

significant in the general meaning of the word). The high variance and unexplained differences 

in means within each temperature group suggest there is another factor affecting the breakloose 

torque. The EDA graphical representations illustrate that exposure time is unlikely the cause of 

dissimilar means. Exposure temperature may have an effect. The purpose of Loctite® 242 is not 

to increase breakloose torque, but to maintain adequate preload in the presence of vibration. 

Breakloose torque may not be the appropriate metric to evaluate the effectiveness of Loctite®

242, and to assess the affect of factors such as exposure time at temperature. While the 

breakloose torque may be affected by temperature that does not necessarily correlate to 

conclusions regarding the effectiveness of Loctite® 242 as a secondary locking feature. 

Figure 7.7-2a. ANOVA on Breakloose Torque versus Exposure Time (200 °F hot case) 

One-way ANOVA: Breakaway Torque versus Time (Hot)

Analysis of Variance for hot breakaway Torque

Source DF SS MS F P

Time hot 9 1099.85 122.21 15.43 0.000

Error 249 1971.78 7.92

Total 258 3071.63

 Individual 95% CIs For Mean

 Based on Pooled StDev

Level N Mean StDev ------- +--------- +--------- +---------

215 26 13.519 3.233 ( --- *---) 

383 26 10.115 3.192 ( --- *--) 

479 26 12.538 2.404 ( ---*-- ) 

575 26 12.038 1.661 ( --*--- ) 

670 26 12.346 2.652 ( --*--- ) 

768 26 11.077 2.952 (---*---) 

862 25 16.040 4.036 ( --*---) 

1000 26 8.038 2.676 ( ---*--) 

1054 26 10.923 2.331 ( --*---) 

1174 26 10.038 2.391 ( --*---) 

 ------- +--------- +--------- +---------

Pooled StDev = 2.814 9.0 12.0 15.0
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Figure 7.7-2b. ANOVA on Breakaway Torque versus Exposure Time (-140 °F cold case) 

Figure 7.7-2c. ANOVA on Breakloose Torque versus Exposure Time (72 °F ambient case) 

One-way ANOVA: Breakaway Torque versus Time (Cold)

Analysis of Variance for Cold Breakaway Torque

Source D F SS MS F P

Time col 9 1417.5 157.5 9.51 0.000

Error 229 3794.5 16.6

Total 238 5212.0

 Individual 95% CIs For Mean

 Based on Pooled StDev

Level N Mean StDev -------- +--------- +--------- +--------

263 24 9.542 3.092 ( ---*----) 

451 23 15.870 4.310 ( ---*----) 

553 24 12.250 3.859 ( ---- *----) 

619 24 13.750 3.848 ( ---*---- ) 

715 24 12.917 2.903 ( ----*----) 

811 24 13.208 4.644 ( ----*---) 

907 24 14.375 6.212 (----*---- ) 

1005 24 13.417 4.149 ( ---*---- ) 

1099 24 18.583 2.781 ( ---- *----) 

1197 24 17.083 3.798 ( ----*--- ) 

 -------- +--------- +--------- +--------

Pooled StDev = 4.071 10.5 14.0 17.5

One-way ANOVA: Breakaway Torque versus Time (ambient)

Analysis of Variance for ambient

Source DF SS MS F P

time amb 3 855.7 285.2 18.16 0.000

Error 79 1240.6 15.7

Total 82 2096.3

 Individual 95% CIs For Mean

 Based on Pooled StDev

Level N Mean StDev ----------+---------+---------+------

48 16 14.313 4.976 (----*----) 

192 24 20.917 3.501 (---*---) 

384 20 24.000 4.713 (---*---) 

480 23 20.174 2.741 (---*----) 

 ----------+---------+---------+------

Pooled StDev = 3.963 16.0 20.0 24.0
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Figure 7.7-3. ANOVA on Breakaway Torque versus Temperature 

Figure 7.7-4a. Dotplot of Torque versus Test Series ACB01 ACB04

ACB02ACB03

HB05HB04HB03HB02HB01HB10HB09HB08HB07HB06

CB06CB07CB05CB04CB03CB02CB08CB09CB10CB01

30

20

10

0

Dotplots of HB05 - ACB03

(group means are indicated by lines)

One-way ANOVA: Breakaway Torque versus Temperature

Analysis of Variance

Source DF SS MS F P

Factor 2 4578.7 2289.4 127.47 0.000

Error 579 10398.7 18.0

Total 581 14977.5

 Individual 95% CIs For Mean

 Based on Pooled StDev

Level N Mean StDev ---+---------+---------+---------+---

hot 260 11.667 3.454 (-*-) 

cold 239 14.092 4.680 (-*-) 

ambient 83 20.181 5.056 (--*--) 

 ---+---------+---------+---------+---

Pooled StDev = 4.238 12.0 15.0 18.0 21.0
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Figure 7.7-4b. Dotplot of Torque versus Exposure Temperature 

7.7.3 Junker Testing 

A study of the loosening resistance of threaded fasteners subjected to dynamic shear was 

performed. A series of tests were performed to provide a comparative assessment of the locking 

performance (or loosening resistance) of NAS1004-28 UNJF-3A hex head screws with: 

1. Standard free-running Helicoil® inserts with Braycote® 601 lubricant. 

2. Locking Helicoil® inserts with Braycote® 601 lubricant. 

3. Standard free-running Helicoil® inserts with Loctite® 242. 

The tests were performed on a Deutsches Institut für Normung (DIN) 65151 or Junker type test 

machine, which provides dynamic shear loading. Twelve tests were performed for each locking 

level. The selected test-machine parameters provides significant loosening with the “standard” 

Helicoil® insert with Braycote® 601 lubricant configuration over a finite number of cycles, 

without causing screws to break for any of the locking levels, so that the performance of the 

secondary locking features can be compared. The tests were performed with the test machine at 

15Hz with a 0.12 inch eccentric, preload at 66 percent yield or 2,400 pounds, and a record length 

of 2,400 cycles. The percent loss of preload was determined after 2,300 cycles for each test run. hot Cold ambient

30

20

10

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Temperature breakloose torque

Dotplots of breakloose by Temperature

(group means are indicated by lines)
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7.7.3.1 Conclusions 

The data and analyses showed that for the conditions tested: 

1. The Standard Helicoil® insert with Loctite® 242 on average provides better locking 

performance than the Locking Heli-coil® insert with Braycote® 601 lubricant and the 

Standard Helicoil® insert with Braycote® 601 lubricant. 

2. The Standard Helicoil® insert with Braycote® lubricant on average has the worse 

locking performance of the three configurations tested. 

7.7.4 Thermal/Vacuum Cyclic Testing 

The NESC conducted some limited thermal vacuum cyclic testing as part of the investigation 

into the use of anaerobic locking compounds in fastening systems. The “Loctite® Investigation 

Thermal Vacuum Cycling Testing” test plan, dated February 9, 2007, and test results are 

provided in Appendix G. 

Simulated bolted joints using Loctite® threadlocker were subjected to thermal cycling in a high 

vacuum environment. The breakloose torque, prevailing torque, as a function of time, were 

recorded post exposure to thermal/vacuum cycling. 

The simulated joint, very similar to that shown in Figure 7.1-1, used NAS1004, 1⁄4-28 UNJF-3A 

bolts to clamp a cylinder to an aluminum base plate. The cylinder materials, aluminum 6061-T6, 

A286, and 15-5 PH were chosen to provide either a CTE null temperature effect or a CTE 

thermal load of approximately ±1000 pounds in the joint. Bolts were installed into various base 

plates containing twenty five simulated fastener joints with Loctite® 242 used as the thread 

locker. Each plate contained ten (10) aluminum cylinders, ten (10) A286 cylinders, and five (5) 

15-5 PH cylinders. Bolts were torqued to produce an initial preload of approximately 650 

pounds force based on a portion of the fasteners being installed with instrumented bolt (joints 

with aluminum cylinders were torque to an average 50 inch-pounds and the joints with stainless 

cylinders were torques to an average of 45 inch pounds torque). Thermal cycling was 

performed in a high vacuum (10-5 torr) environment between ±100°C. 

The approximate thermal cycle used is shown in Figure 7.7-5, and the test plate removal 

schedule is shown in Figure 7.7-6. 
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Figure 7.7-5. Thermal Cycle Profile 

Figure 7.7-6. Test Article Removal Schedule 
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At specified time intervals, a test plate was removed from the thermal/vacuum environment. 

Breakloose and running torque results are shown in Table 7.7-5. 

Table 7.7-5. Breakloose and Running Torque Results for Thermal Vacuum Cyclic Testing of 

Preloaded Fasteners plus Loctite® with aluminum and Stainless Steel Cylinders 

Test Plate Number (order of removal from chamber) 2 1 3 4 5 6 7 8 9 10

Total time in Chamber (hours) 192 384 480 576 648 768 816 912 1008 1104

Number of thermal cycles 18 42 55 69 83 91 103 116 130 142

Avg. Installation Torque (Aluminum Cylinders) 50 50 50 50 50 50 50 50 50 50

Avg. Installation Torque (Stainless cylinders) 45 45 45 45 45 45 45 45 45 45

Avg. Breakloose torque (in-lbs) 57.1 48.8 51.4 50.7 52.7 51.6 52.5 55.3 53.9 52.8

Avg. Breakloose torque Standard Deviation (in-lb) 4.6 9.6 4.8 4.4 3.4 4.5 5.0 3.9 4.2 3.6

Avg. Running Torque for 2 Complete Rotations (in-lb) 15.7 14.7 14.2 14.0 11.0 8.9 8.2 9.8 8.9 9.2

Avg. Running torque StDev for 2 Complete Rotations (inlb) 3.0 3.7 2.7 2.3 4.4 2.0 2.2 1.8 2.2 1.8

 

Avg. Running Torque for 1st Rotation Only (in-lb) 18.5 17.4 16.7 16.8 12.5 10.2 10.1 11.4 10.7 11.4

Avg. Running Torque StDev for 1st Rotation Only (in-lb) 3.8 4.4 2.7 2.3 4.9 2.6 2.6 2.3 2.8 2.3

Avg. Running Torque for 2nd Rotation Only (in-lb) 12.9 11.9 11.7 11.2 9.5 7.5 6.3 8.2 7.1 7.1

Avg. Running Torque StDev for 2nd Rotation Only (in-lb) 2.1 3.0 2.6 2.4 3.8 1.5 1.9 1.4 1.6 1.3

Results: The breakloose torques were similar to the installation torques. There appears to be no 

effect of thermal cycling between minus 100°C and 100°C in a high vacuum environment of 10-5

torr over time on the performance of Loctite® as a thread locker for the number of thermal 

cycles tested. 

7.8 Human Factors review of Application Process for LLCs in ISS 

Hardware 

Loctite® is an LLC, although there are other brands of LLC’s. “LLC” and the trade name 

“Loctite®” are used interchangeably. The three standards below were reviewed and 

inconsistencies/incongruities among the standards assessed, including descriptions of 

activators/primers, cure time and the activator/primers, activator/primers and inactive metals, and 

the application of LLCs on fastening hardware. Current information obtained from the Loctite®

manufacturer regarding certain application features was also assessed. Details of the review are 

included as Appendix H. 

MIL-S-22473E “Military Specification: Sealing, Locking, and Retaining Compounds: (Single 

Component)” (dated 12 Apr 1983, and cancelled 21 Jan 2004) 

MIL-S-46163A “Military Specification: Sealing, Lubricating and Wicking Compounds: 

Thread-Locking, Anaerobic, Single-Component” (dated 12 Jul 1983, and inactivated for new 

design 23 Mar 2001) 

ASTM D5363-03 “Standard Specification for Anaerobic Single-Component Adhesives (AN)” 

(dated Dec. 2003, and corrected Aug 2006)
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7.9 Loctite® Application Process Comparison 

The standards listed below were reviewed relative to their use for the application of LLCs to 

flight hardware. The review included; (1) how activator/primer is described in the documents, 

(2) a comparison of the documents, (3) how LLC’s are described in the documents, and, (4) 

results of field observations of applying Loctite® during ISS rework operations. Details of the 

review are included as Appendix I. 

1. Boeing Document BAC 5011, “Application of Retaining Compounds” (Dec-86) 

2. Boeing Document Dwg. 683-13000 “Hatch Assembly” (May, 2005) 

3. Lockheed Martin (Michoud Oprs) Document STP 2009B, “Locking and Sealing 

Compounds, Application of” (Sep-04) 

4. Rockwell Document MA0106-333, “Application of Locking and Retaining Compound to 

Threaded Electrical, Hardware and Mechanical Fasteners” (Dec-85) 

5. Boeing Huntington Beach Document MA0106-333, “Application of Locking and 

Retaining Compound to Threaded Electrical, Hardware and Mechanical Fasteners” (Apr04) 

7.10 Literature Review 

A literature review (see Appendix J) was performed which provides an overview on the selfloosening of threaded fasteners, which specifically includes bolted joints. The review includes a 

brief chronological overview of research reports related to the self-loosening of fasteners due to 

vibration. Then a summary of parameters that have been identified by the authors of the research 

articles are summarized and followed by a section which presents a brief overview of some 

testing machines that have been used. This literature review was organized to be only a review 

of the topic, and details on any of the testing and research that was conducted may be found in 

the original articles that are identified in Section 14.0. 

7.11 Questions/Discussions with Henkel Loctite®

In summary, this question/answer exchange proved to be valuable in helping the team’s 

understanding of Loctite® threadlockers and provided clarification information for numerous 

company procedure documents that the team evaluated. The information provided in Appendix 

B is as received and unedited so that the information provided by Henkel Loctite® was not 

changed. 
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8.0 Observations, Findings, and NESC Recommendations 

The findings, observations, and recommendations provided in this investigation apply to the 

anaerobic LLCs Loctite® 242 and 271. No other anaerobic LLCs were evaluated for this 

investigation. 

8.1 Observations 

The following observations were identified: 

O-1. Higher preloads help to resist vibration loosening regardless of the type of locking feature 

(e.g., LLC, prevailing torque type, or none) tested. 

O-2. Loctite® 242 and 271 contribute to prevent loosening (Phase zero testing). 

O-3. Preload level has no effect on the breakaway strength of fully cured Loctite® 242 and 

271 (zero load wedge testing). 

O-4. Breakaway strength is affected by hole type, being lower in blind holes than in thru holes 

(zero load wedge testing). 

O-5. LLC cure time is longer for blind holes than for thru holes. 

O-6. Breakaway strength was higher when the fastening system hardware surfaces were 

adequately cleaned, chemically activated, and both female and male threads were 

sufficiently coated with the anaerobic LLC. 

O-7. Using a Junkers test, a standard Heli-coil® insert with Loctite® 242 provided better 

locking performance than a locking Heli-coil® insert with Braycote® 601 lubricant. 

O-8. LLCs will take significantly longer to fully cure and the timeframe is highly 

unpredictable when no activator is used on inactive/less active metals like stainless and 

titanium. 

O-9. Humidity has no effect on breakaway strength when LLCs are applied to both female and 

male substrate surfaces. 

8.2 Findings 

The following findings were identified: 

F-1. Loctite® 242 and 271 provide resistance to vibration loosening at least as good as that 

provided by prevailing torque type locking inserts. 
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F-2. Military and industry specifications regarding LLCs are inconsistent and somewhat 

contradictory in their treatment of LLCs. Proper application processes must be 

developed for using LLCs. 

F-3. Factors that improve cure of LLCs include: substrate cleanliness, proper surface 

activation, tighter thread class, use of thru hole instead of blind hole, and application of 

sufficient LLC to both the female and male substrate surfaces to eliminate all air in thread 

gap. 

F-4. Loctite® breakloose torque performance is degraded when used over fastening system 

hardware with DFL coatings applied. 

8.3 NESC Recommendations 

NESC recommendations to the NASA engineering community for the use of the specific 

anaerobic liquid locking compounds addressed in this report follow: 

R-1. Accept Loctite® 242 and 271 for use as a secondary locking feature for ISS hardware 

when application processes that produce sufficient cure for the substrates to which they 

are applied have been developed. (F-1, F-2, and F-4)

R-2. Develop LLC application processes that produce sufficient cure of the LLC for the 

substrates to which applied. (F-2)

a. Develop procedures and tests that verify sufficient cure of the LLCs. (F-2) 

b. Prevent contamination of LLCs prior to, during and after application processes. (F-3)

c. Use activators on inactive/less active substrates (e.g., stainless steel, titanium) and 

apply to both female and male fastening system components. (F-3)

d. Determine the torque-tension behavior of fastening system hardware that will use 

LLCs. The torque-tension behavior should be characterized to load levels greater 

than those required for fastener installation (e.g., typically 50-75% of the load 

carrying capability of the fastener in pounds). (F-2)

e. LLCs shall be applied to both the female and male threaded surfaces during 

application processes. (F-3)

f. Clean and activate female and male substrate surfaces prior to applying LLCs. (F-3)
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g. Do not use LLCs on hardware that has dry film lubrication applied to either female or 

male threaded surfaces. (F-4)

R-3. NASA Office of the Chief Engineer should revise NASA-STD-6016 Standard Materials 

and Processes Requirements for Spacecraft Section 4.2.6.5.1 Liquid Locking Compound 

to reflect the data and conclusions of this report. (All Findings)

9.0 Alternate Viewpoints 

It may be that some alternative viewpoints exist; however, no alternative viewpoints were 

reported to the NESC team or by NESC team members for incorporation into this report. 

10.0 Other Deliverables 

There are no other deliverables for this effort. 

11.0 Lessons Learned 

LL-1. When Loctite® cures sufficiently, it provides secondary locking of threaded fasteners at 

least as good as prevailing torque locking fasteners. 

LL-2. Loctite® should be applied to both male and female threads in sufficient quantity to 

eliminate air in the thread gap (cure depends on absence of oxygen). 

LL-3. Activator / primer should be used prior to application of Loctite® threadlocker (improves 

cure and reduces cure time when used with non-active thread material). 

LL-4. Threaded surfaces should be cleaned of grease and contaminates before application of 

Loctite® activator / primer and Loctite® threadlocker. 

LL-5. Loctite® should not be used with fastener threads coated with DFL. 

LL-6. Loctite® cure time is longer when used with blind holes than with thru holes. 

LL-7. Tighter hole tolerance improves Loctite® breakaway torque. 

LL-8. Loctite® cure is not a function of preload. 
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12.0 Definition of Terms 

Corrective Actions 

Changes to design processes, work instructions, workmanship practices, training, inspections, 

tests, procedures, specifications, drawings, tools, equipment, facilities, resources, or material that 

result in preventing, minimizing, or limiting the potential for recurrence of a problem. 

Finding 

A conclusion based on facts established by the investigating authority. 

Lessons Learned 

Knowledge or understanding gained by experience. The experience may be positive, as in a 

successful test or mission, or negative, as in a mishap or failure. A lesson must be significant in 

that it has real or assumed impact on operations; valid in that it is factually and technically 

correct; and applicable in that it identifies a specific design, process, or decision that reduces or 

limits the potential for failures and mishaps, or reinforces a positive result. 

Observation 

A factor, event, or circumstance identified during the assessment that did not contribute to the 

problem, but if left uncorrected has the potential to cause a mishap, injury, or increase the 

severity should a mishap occur. Alternatively, an observation could be a positive 

acknowledgement of a Center/Program/Project/Organization’s operational structure, tools, 

and/or support provided. 

Problem 

The subject of the independent technical assessment/inspection. 

Proximate Cause 

The event(s) that occurred, including any condition(s) that existed immediately before the 

undesired outcome, directly resulted in its occurrence and, if eliminated or modified, would have 

prevented the undesired outcome. 

Recommendation 

An action identified by the assessment team to correct a root cause or deficiency identified 

during the investigation. The recommendations may be used by the responsible 

Center/Program/Project/Organization in the preparation of a corrective action plan. 
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Root Cause 

One of multiple factors (events, conditions, or organizational factors) that contributed to, or 

created the proximate cause and subsequent undesired outcome and, if eliminated or modified, 

would have prevented the undesired outcome. Typically, multiple root causes contribute to an 

undesired outcome. 

13.0 Acronyms List 

ALMA Aerospace Locknut Manufacturers Association 

ANSI American National Standards Institute 

ARC Ames Research Center 

ASTM American Society for Testing and Materials 

ATK Alliance Techsystems, Inc. 

CTE Coefficient of Thermal Expansion 

DFL Dry Film Lubricated 

DIN Deutsches Institut für Normung 

ESNA Elastic Stop Nut Corporation of America 

ESP External Stowage Platform 

ESPAD External Stowage Platform Attachment Device 

EVA ExtraVehicular Activity 

FRAM Flight Release Attachment Mechanism 

GSFC Goddard Space Flight Center 

ICC Integrated Cargo Carrier 

ISS International Space Station 

JSC Johnson Space Center 

KSC Kennedy Space Center 

LaRC Langley Research Center 

LLC Liquid Locking Compound 

MEK Methyl-Ethyl-Ketone 

Mil-DTL Military Detailed Specification 

Mil-S Military Specification 

MSFC Marshall Space Flight Center 

NASM National Aerospace Standard (former Military Standard) 

NESC NASA Engineering and Safety Center 

NRB NESC Review Board 

QA Quality Assurance 

TDT Technical Discipline Team 

UCP Unpressurized Cargo Pallet 
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14.0 References 

1. Anon. “Fastener Loosening: The Causes Part I,” Assembly Engineering 27 (2) (February 

1984): pp. 16-18. 

2. Basava, S. and D. P. Hess. “Bolted Joint Clamping Force Variation Due to Axial 

Vibration,” Journal of Vibration and Sound 210 (2) (1998): pp. 255-265. 

3. Bickford, James H. An Introduction to the Design and Behavior of Bolted Joints. New 

York and Basel: Marcel Dekker, Inc., 1990. 

4. Bickford, James H. “Fastener Groups Seek Answers to Bolted-Joint Problems,” Machine 

Design (July 1984): pp. 77-80. 

5. Bickford, James H. “That Initial Preload – What Happens to it?” Mechanical Engineering

105 (10) (October 1983): pp. 57-61. 

6. Bolt Science. “Bolt Science: Solutions to Bolting Problems - Vibration Loosening of 

Bolts and Threaded Fasteners,” Bolt Science Limited (2006) 

http://www.boltscience.com/pages/ vibloose.htm; Internet; accessed 20 Mar. 2006. 

7. Charles, William J. “Use of Adhesives and Sealants on Mechanical Fasteners to Improve 

Performance,” Adhesives Coatings and Sealants Division, 3M UK PLC. Bracknell, Berks 

Network Events (1985): pp. 165-176. 

8. Chen, J-H., S-C. Hsieh, and A-C. Lee. “The Failure of Threaded Fasteners Due to 

Vibration,” Journal of Mechanical Engineering Science 219 (C) (2005): pp. 299-314. 

9. Crane, Ryan. American Society of Mechanical Engineers (ASME). Private 

Correspondence, 01 May 2006. 

10. Deutsches Institut für Normung (DIN) EN ISO 10964. 

11. Deutsches Institut für Normung (DIN) 54454. 

12. Deutsches Institut für Normung (DIN) 65151. 

13. Dong, Yubo and Daniel P. Hess. “Accelerated Vibration Life Tests of Threadlocking 

Adhesive,” Journal of Aircraft 35(5) (September – October 1998): pp. 816-820. 

14. Dong, Yubo and Daniel P. Hess. “The Effect of Threaded Dimensional Conformance on 

Vibration-Induced Loosening,” Journal of Vibration and Acoustics 121 (April 1999): pp. 

209-213. 

15. Dong, Yubo and Daniel P. Hess. “Optimum Placement of Bolts in Structures Based on 

Dynamic Shear,” Journal of Sound and Vibration 217(2) (1998): pp. 396-404. 
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16. Dong, Yubo and Daniel P. Hess. “Shock Induced Loosening of Dimensionally NonConforming Threaded Fasteners,” Journal of Sound and Vibration 231(2) (2000): pp. 

451-459. 

17. Gillis, Jim. “Threads Get a Grip on Shock, Vibration,” Machine Design 76(1) (January 8 

2004): pp. 85-86. 

18. Glackin, J. J. and E. F. Gowen, Jr. Evaluation of Fasteners and Fastener Materials for 

Space Vehicles. Standard Pressed Steel Company, Jenkintown, PA, National Aeronautics 

and Space Administration (NASA) Marshall Space Flight Center (MSFC), December 

1965. Contract No. NAS 8-11125, NASA CR 357. 

19. Goodier, J. N. and R. J. Sweeney. “Loosening by Vibration of Threaded Fastenings,” 

Mechanical Engineering 67 (December 1945): pp. 798-802. 

20. Hardiman, Russell J. Anaerobic Adhesives: A Viable Fastener Locking System. Society of 

Manufacturing Engineers, 1974. AD74-429. 

21. Hard Lock Industry Co., Ltd. “Testing of Various Types of Hard Lock Nut,” Hard Lock 

Industry Co., Ltd. Online. Home page on-line. Available from http://www.hardlock.co.jp/ 

en/hl/03.php; Internet; accessed 30 March 2006. 

22. Haviland, Girard S. “Designing With Threaded Fasteners,” Mechanical Engineering 105 

(10) (October 1983): pp. 16-31. 

23. Haviland, Girard S. “Unraveling the Myths of the Fastener World,” Society of 

Automotive Engineers (SAE) International Automotive Engineering Congress (February 

1981) Document 810509. 

24. Haviland, Girard S. Machinery Adhesives for Locking, Retaining, and Sealing. New York 

and Basel: Marcel Dekker, Inc., Loctite® Corporation Newington, Connecticut, 1986. 

25. Hess, Daniel P. “Counter-Threaded Spring-Actuated Lock-Fasteners,” Journal of 

Mechanical Design Technical Briefs 124 (September 2002): pp. 582-585. 

26. Hess, Daniel P. and K. Davis. “Threaded Components Under Axial Harmonic Vibration, 

Part I: Experiments,” Journal of Vibration and Acoustics 118 (July 1996): pp. 417-422. 

27. Hess, Daniel P. and S. V. Sudhirkashyap. “Dynamic Loosening and Tightening of a SingBolt Assembly,” Journal of Vibration and Acoustics 119 (July 1997): pp. 311-316. 

28. Hess, Daniel P., Srinivas Basava, and Ingrid A. Rasquinha. “Variation of Clamping Force 

in a Single-Bolt Assembly Subjected to Axial Vibration,” DE. 90 Elasto-Impact and 

Friction in Dynamic Systems ASME (1996): pp. 97-102. 
NASA Engineering and Safety Center 

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29. Hess, Daniel P. “Vibration and Shock Induced Loosening,” In John H. Bickford and 

Sayed Nassar: Handbook of Bolts and Bolted Joints, 757-824. New York: Marcel Dekker 

Inc., 1998. 

30. Holland, M. and D. Tran. “FEM Modeling of Threaded Fastener Loosening Due to 

Dynamic Forces,” Proceedings of the Eighth International Conference on Civil and 

Structural Engineering Computing, Civil-Comp Press, Stirling, Scotland, 2001. 

31. Ibrahim, R. A. and C. L. Pettit. “Uncertainties and Dynamic Problems of Bolted Joints 

and Other Fasteners,” Journal of Sound and Vibration 279 (2005): pp. 857-936. 

32. Jiang, Yanyao, Ming Zhang, and Chu-Hwa Lee. “A Study of Early Stage Self-Loosening 

of Bolted Joints,” Transactions of the American Society of Mechanical Engineers 

(ASME) 125 (September 2003): pp. 518-526. 

33. Jiang, Yanyao, Ming Zhang, Tae-Won Park, and Chu-Hwa Lee. “An Experimental Study 

of Self-Loosening of Bolted Joints,” Journal of Mechanical Design 126 (September 

2004): pp. 925-931. 

34. Junker, Gerhard H. “Criteria for Self-Loosening of Fasteners Under Vibration,” Aircraft 

Engineering (October 1972): pp. 14-16. 

35. Junker, Gerhard H. “Criteria for Self-loosening of Fasteners Under Vibration,” Aircraft 

Engineering 42 (2) (February1973): pp. 20-23. 

36. Junker, Gerhard H. “Criteria for Self Loosening of Fasteners Under Vibration,” Aircraft 

Engineering (January 1973): pp. 12-17. 

37. Junker, G. H. “New Criteria for Self-Loosening of Fasteners Under Vibration,” Society 

of Automotive Engineers (SAE) International Automotive Engineering Congress 

(January 1969): pp. 314-335. 

38. Kerley, James J., “An Application of Retroduction to Analyzing and Testing the Backing 

Off of Nuts and Bolts During Dynamic Loading,” National Aeronautics and Space 

Administration (NASA) Scientific and Technical Information Office, Goddard Space 

Flight Center (GSFC) 1987. NASA TM 4001. 

39. Kerley, James J. “The Use and Misuse of Six Billion Bolts Per Year” Society for 

Machinery Failure Prevention Technology, Thirty-fifth Meeting, Session IV: System 

Assessment and Response. 

40. Kerley, James. “Nuts and Bolts: Practical Applications for Bolts and Nuts for the 

Designer” National Aeronautics and Space Administration (NASA) Goddard Space 

Flight Center (GSFC) TM 109783 January 1980. 

41. Kerley, James. “Report on Dynamic and Static Testing of Spiralock Nuts,” National 

Aeronautics and Space Administration (NASA) Goddard Space Flight Center (GSFC) 
NASA Engineering and Safety Center 

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Engineering Services Division, Environmental Test and Integration Branch, Structural 

Dynamics and Electromagnetic Test Section, September 1984. 

42. Kumakura, Susumu, Syuzi Hosokawa, and Toshiyuki Sawa. “On the Self-loosening of a 

Bolts Nuts Under Repeated Tensile Loads,” American Society of Engineering (ASME) 

Pressure Vessels and Piping (PVP) 305, Current Topics in Computational Mechanics, 

(1995): pp. 119-124. 

43. Light, D. J. “Vibration Loosening of Threaded Fastenings,” Institution of Mechanical 

Engineers Chartered Mechanical Engineer (CME) 30 (5) (May 1983): pp. 56-60. 

44. Loctite. “Junker Test Principle,” Loctite Online. Home page on-line. Available from 

http://www.loctite.be/wwdh/us/i061ch03.htm; Internet; accessed 30 March 2006. 

45. Nakahara,Takeshi, Masaaki Yamamoto, Yusuke Ohya, and Masaaki Okuma. “Bolt 

Loosening Detection Using Vibration Characteristics of Thin Plate with Piezoelectric 

Elements,” Smart Structures and Materials SPIE 5391 (2004): pp. 667-678. 

46. Nassar, S. A. and B. A. Housari. “Self-loosening of Threaded Fasteners Due to Cyclic 

Transverse Loads,” American Society of Mechanical Engineers (ASME) Pressure Vessels 

and Piping Division Conference Denver, Colorado, USA, PVP2005-71577 (July 17-21, 

2005): pp. 169-187. 

47. Nord-Lock. “Junker Test Principle,” Nord-Lock Online. Home page on-line. Available 

from http://www.nord-lock.com/default.asp?url=6.16.37; Internet; accessed 30 March 

2006. 

48. Pai, N. G. and Daniel P. Hess. “Dynamic Loosening of Threaded Fasteners,” Noise and 

Vibration Worldwide (February 2004): pp. 13-19. 

49. Pai, N. G. and Daniel P. Hess. “Experimental Study of Loosening of Threaded Fasteners 

Due to Dynamic Shear Loads,” Journal of Sound and Vibration 253 (3) (2002): pp. 585-

602. 

50. Pai, N. G. and Daniel P. Hess. “Influence of Fastener Placement on Vibration-Induced 

Loosening,” Journal of Sound and Vibration 268 (2003): pp. 617-626. 

51. Pai, N. G. and Daniel P. Hess. “Three-dimensional Finite Element Analysis of Threaded 

Fastener Loosening Due to Dynamic Shear Load,” Engineering Failure Analysis 9 

(2002): 383-402. 

52. Pearce Jr., M. B. “A Study of Vibration-Resistant Fasteners,” Society of Automotive 

Engineers (SAE) Document No. 730825 (1973): pp. 1-5. 
NASA Engineering and Safety Center 

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53. Ramey, Ed G. and Robert C. Jenkins. Experimental Analysis of Thread Movement in 

Bolted Connections Due to Vibrations, Alabama: Harbert Engineering Center, Civil 

Engineering Department, Auburn University, NAS8-39131. 

54. Sakai, Tomotsugu. “Investigations of Bolted Loosening Mechanisms, 1st Report: On the 

Bolts of Transversely Loaded Joints,” Bulletin of the Japan Society of Mechanical 

Engineers (JSME) 21(159) (1978): pp. 1385-1390. 

55. Vinogradov, O. and X. Huang. “On a High Frequency Mechanism of Self-Loosening of 

Fasteners,” American Society of Mechanical Engineers (ASME) Design Engineering 

Division Publication DE, 18 (4) Vibration Analysis – Techniques and Applications 

Conference (1989): pp. 131-137. 

56. Wineman, Steve. American National Standards Institute (ANSI), Director of 

Standardization and Testing. Private Correspondence, 25 April 2006. 

57. Yamamoto, Akira and Shinji Kasei. “A Solution for Self-Loosening Mechanism of 

Threaded Fasteners Under Transverse Vibration,” Bulletin Japan Society of Prec. 

Engineering 18 (3) (September 1984): pp. 261-266. 

58. Yost, V. H. “Random Vibration and Torque Tests of Fasteners Secured With Cable, 

Room Temperature Vulcanized (RTV) Rubber, and Closed Cell Foam to Support the 

Launch of STS-82,” National Aeronautics and Space Administration (NASA) Marshall 

Space Flight Center (MSFC), August 1997. NASA TM 108539. 

59. Zhang, Ming, Yanyao Jiang, and Chu-Hwa Lee. “An Experimental Investigation of the 

Effects of Clamped Length and Loading Direction on Self-Loosening of Bolted Joints,” 

American Society of Mechanical Engineers (ASME) Pressure Vessels and Piping (PVP) 

478, Analysis of Bolted Joints, July 25-29, San Diego, California, USA, PVP2004-2631. 

(2004): pp. 129-136. 

60. Zhang, Ouqi. “Discussions on Behavior of Bolted Joints in Tension,” Transactions of the 

American Society of Mechanical Engineers (ASME) 127 (May 2005): pp. 506-510. 

61. Zhang, Ouqi and Jason A. Poirier. “New Analytical Model of Bolted Joints,” Journal of 

Mechanical Design 126 (July 2004): pp. 721-728. 

Volume II: Appendices 

Appendix A. Space Flight Environments for ISS 

Appendix B. Question and Answer meeting with Loctite® Representative 

Appendix C. Evaluation of Anaerobic Locking Compounds, Tensile Testing, Torque Tension 

Testing, and Breakloose and Running Torque Testing 

Appendix D. CTE Effects of Fastener Mechanical Loads 

Appendix E. NASM1312-7 Vibration Testing Test Plan 
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Appendix F. Comparison of Secondary Locking Features for Threaded Inserts, July 2007 

Appendix G. Thermal/Vacuum Cyclic Testing Plan and Results 

Appendix H. Human Factors Review of Application Process for Liquid Locking Compounds 

(LLC) in ISS Hardware 

Appendix I. Loctite® Application Process Comparison 

Appendix J. Literature Review of the Self-Locking of Threaded Fasteners 
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VOLUME II: Appendices 

Appendix A. Space Flight Environments for ISS 

Space Flight Environments for ISS

EVA Environments 

Environment 

Factor 

Source Worst Case 

Value 

Comments Evaluation 

Rationale 

Natural Ambient 

Atmosphere 

SSP- 30425 2.8 x 10-10 torr Neutral 

atmosphere only 

Non Factor - Vacuum 

only not degrading 

Induced Ambient 

Atmosphere 

Vehicle 

configuration 

and flight 

attitude 

dependent: 

requires detailed 

rarefied gas 

dynamic 

calculations with 

NASAN II 

(Boeing ISS 

Environments) 

Ranges from 

> 10-4 torr to 

<10-10 torr: 

1) Vehicle 

interaction 

with ambient 

atmos. 

2) Vehicle 

outgassing 

3) Plumes, vents 

and dumps 

Vacuum only under 

evaluation for cure 

Temperature under 

evaluation – Product 

information states use 

from -65°F to 300°F 

Solar UV/VUV SSP-30425 

7.2 

9.5 x 10-3

W/m2

Photon 

Wavelength = 150 

nm to 10 nm 

Non Factor – Loctite®

protected by metallic 

fastener 

Nominal Solar Xrays SSP-30425 5 x 10-5 W/m2 Photon 

Wavelength = 

1 nm to 10 nm 

Non Factor – Loctite®

protected by metallic 

fastener 

Flare Solar X-rays SSP-30425 1 x 10-4 W/m2 Photon 

Wavelength = 0.1 

nm to 1 nm 

Non Factor – Loctite®

protected by metallic 

fastener 

Atomic Oxygen SSP-41000 and 

SSP-30425 

(MSIS) 

1.5 x 1019

atoms/cm2

 

per day (24 

hrs)

Forward facing 

vehicle surfaces 

only – near 0 in 

wake 

Non Factor – Loctite®

protected by metallic 

fastener 

Ionizing Radiation 

2.1 x 10-4 g/cm2 

(surface) 

SSP-30512 Rev. 

C 

3.1.2-2 

1.1 x 104

Rads(Si) 

per day (24 

hrs) 

Mostly trapped 

electrons 

Slab configuration 

Non Factor – Loctite®

protected by metallic 

fastener 

Ionizing Radiation 

0.11 g/cm2

 

(approx. 0.5 mm 

Al)

SSP-30512 Rev. 

C 

3.1.2-2 

7.3 Rads (Si) 

per day (24 

hrs) 

Mostly trapped 

electrons 

Slab configuration 

Non Factor – Loctite®

protected by metallic 

fastener 
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Environment 

Factor 

Source Worst Case 

Value 

Comments Evaluation 

Rationale 

Ionizing Radiation 

0.5 g/cm2

 

(approx. 1.8 mm 

Al)

SSP-30512 Rev. 

C 

3.1.2-2 

0.6 Rads (Si) 

per day (24 

hrs) 

Mostly trapped 

electrons 

Slab configuration 

Non Factor – Loctite®

protected by metallic 

fastener 

Ionizing Radiation 

3.5 g/cm2

 

(approx. 12 mm 

Al)

SSP-30512 Rev. 

C 

3.1.2-2 

0.04 Rads (Si) 

per day (24 

hrs) 

Mostly trapped 

protons 

Slab configuration 

Non Factor – Loctite®

protected by metallic 

fastener 

External 

Contamination 

SSP-30426 

3.5.1 

2.7 x 10-9

g/cm2

per day 

Depends on 

location and line 

of site to sources 

Non Factor – cured 

Loctite® stable, small 

amounts used 

On-Orbit 

Humidity 

SSP-30425 

(MSIS) and 

SSP-30233 

0 percent worst case = 

nominal 

Non Factor – Product 

information states 

Loctite® can be used 

underwater after cure 

 
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Appendix B. Question and Answer meeting with Loctite®

Representative 

Q&A from Brian Jensen to Loctite®.

Dialogues from September and November 2006 Combined (1/18/07).

1. Two of the Mil standards that are important to us are MIL-S-46163 and MIL- S-22473 (now 

cancelled, but superseded by ASTM D5363). With regard to Loctite® 242, Loctite® 2440 and 

Loctite® 271, are these products qualified to the above standards or is there any correlation 

between the Loctite® products and Mil standards in general? 

A1. I have attached a mil spec listing. 2440 is not tested to any 

mil spec. 242 & 271 both are tested to MIL-S-46163A for existing designs. 

(See attached file: MILITARY LISTING '06.doc) attached to original document 

2. Please clarify the role of the Primer N, Primer T, etc. Does it act as a primer for 

improved surface bonding, as an activator for the Loctite® cure, or both? Discuss the 

requirements/benefits/limitations of using the primers with regard to the composition of the 

fastener, in particular steel, stainless steel, titanium, aluminum, or plastic. Loctite® literature 

indicates that when the primer/activator is used, the strength of the final bond on steel substrate 

(indicated by "percent full strength on steel") is lower than that without primer/activator although 

the time for cure is reduced. Please clarify this data.

A2. One of the main functions of the primer is to ensure full cure in 24 hours at room 

temperature. The primer puts a layer of metal ions down on the part to accelerate the cure on 

"inactive metals" which are defined as any protective coatings such as stainless steel, titanium, 

platings, anodized aluminum and galvanized steel. The threadlockers cure in the absence of air 

and metal ions are a catalyst in curing them. 7649 contains copper salt & 7471 contains an 

amine and these serve that function. The strength may be lower on active metals when a primer 

is used because it accelerates the crosslinking of the polymer versus using no primer. However, 

its function on inactive metals like stainless steel is different in the sense that ensures full cure in 

24 hours. If no primer is used on inactive metals like stainless, most of the threadlockers will 

take significantly longer to fully cure and the timeframe is highly unpredictable. It could take 2-

3 weeks to fully cure without a primer. 

The real question becomes how extreme are the service conditions and when do you want to put 

the parts back in service? 
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3. What are your thoughts/position on the reuse of fasteners/and or inserts with previously 

cured Loctite® in the threads? How would you recommend cleaning the threads? NASA has 

used "non-cutting taps" to clean previously cured Loctite®. Is this method recommended? With 

regard to re-use of fasteners previously containing Loctite®, after cleaning, how well does new 

Loctite® bond to old remnants of Loctite® and should the same Loctite® product be re-used or 

can another be substituted? 

A3. The cleaner the threads, the better, prior to reuse. If you have some residue left, the new 

product should adhere to the old, whether it's the same product or a different threadlocker. 

Aggressive solvents like methylene chloride or methyl ethyl keytone are used and often the 

threads are wire brushed as well. The substitution of new hardware of course is another option. 

You'll have to test to determine suitability for reuse if you cannot adequately remove all old 

residue and compare the results versus a control or the first application results. 

4. Can you provide a performance comparison between Loctite® 242 and Loctite® 2440? 

A4. 242 versus 2440. I would review the attached TDS's. Both are medium strength products 

and 2440 is a newer generation product that cures faster and provides primerless adhesion to 

most "inactive metals", unlike 242. 

(See attached file: 242-EN.pdf)(See attached file: 2440-EN.pdf) these were attached to original 

5. Do you have any information on Loctite® performance (curing, break-loose torque) as a 

function of the installation preload? Does Loctite® cure and provide adequate back-off 

prevention when installed in a fastener with just sufficient seating torque (hand tight)? Does 

applied preload effect bonding/cure sensitivity of Loctite® differently as a function of fastener 

and mating thread material or class of thread (class 2 versus class 3)? 

A5. The TDS's may answer this in part. Breakaway values reflect the strength of the product 

alone, on unseated fasteners. Breakloose reflects a seated fastener. Is the product sufficient for 

finger tightened assemblies? Every application is different and I would imagine it is in some 

cases, but not others. This question needs to take into consideration how extreme the service 

conditions are. I don't believe the applied preload will affect the bonding/curing sensitivity of 

the threadlocker although the strength of the product will vary from type metal to the next. Here 

you'll have to do some internal testing for different scenarios. 

6. Is Loctite®’s strength sensitive to vacuum and/or or thermal cycling between the limits 

described in the product specifications as a function of time of exposure? 
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A6. This question in relation to thermal cycling is best answered by reviewing the Heat Aging 

graphs on individual TDS's. If under constant vacuum, the products will continue to outgas after 

cure. None of the products tested by NASA in the past met the requirements for both TWL 

percent & CVCM percent limits. Then again, the products are used in minute amounts in a tight 

space and this does not reflect the NASA cold plate test. Testing under actual service conditions 

would be recommended. 

7. Do you have any test data/information on use of Loctite® on fasteners with Dry Film 

Lubricants (DFL)? Will Loctite® adhere/bond to DFL? If so, at what strength level compared to 

ferrous metals? If not, do you have recommendations on effective cleaning methods of DFL? 

Also, please discuss the effect of oils and rust inhibitors on the performance of Loctite®. 

A7. There is no test data on the use of threadlockers with dry film lubricants. I would imagine 

they'll adhere to the DFL, but this will need to be tested to determine strength if both are used 

simultaneously. I would contact the manufacturer of the DFL and ask they what they suggest for 

removal. All products are not the same. Oil-free surfaces are recommended for most 

threadlockers. If a rust inhibitor contains nitrites, this can inhibit the cure of threadlockers. This 

should be removed prior to use if so. 

8. Do you have any test data/information on Loctite® bonding to aluminum threads? 

A8. There is no test data on aluminum threads. 

9. Is there a filler in the Loctite® 271 that causes the significant increase in running torque 

after the initial break-loose torque is realized? Is this increase in running torque a consistent and 

repeatable performance parameter for the material? If this effect is not the result of a filler, is it a 

result of a higher modulus or hardness of the Loctite® 271 compared to the Loctite® 242? 

A9. Higher prevailing torque values are more a function of the toughness of the monomer base 

& also a function of the fact that the product forms a tighter matrix when it crosslinks versus 

some of the other threadlockers. This should be consistent and repeatable, especially with 

substrates where you obtain high strength in the first place. All threadlockers are high modulus, 

low flex formulations, but some products just exhibit higher prevailing after the initial break due 

to monomer functionality. 

10. What is the cure time for Loctite® 242, Loctite® 271, and Loctite® 2440 and can this be 

accelerated by temperature and/or vacuum? Can you provide time based strength curves or other 

data for these products on different substrates with and without Primer? 
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A10. The full cure for all three (3) products is 24 hours at room temperature. The fixture time 

will vary from one substrate to the next and one thread size to the next. Refer to the TDS's for 

reference data. You can accelerate the cure via heat if this sees 250 ̊F for 1 hour or temperatures 

as low as 150 ̊F for 3 hours. Vacuum conditions won't accelerate the cure. 

11. What are the effects of humidity on the cure process for these products?

A11. Generally, humidity won't affect cure parameters. These are not moisture activated 

products. Any data we have would be presented on the TDS. 

12. Do you have any data on Loctite® offgassing in an ambient (Earth) or vacuum (Space) 

environment for properly cured product? 

A12. Outgassing under vacuum...no data for 2440 (never tested by NASA). 242 - 4.39 percent 

TWL & 0.00 percent CVCM. 271 - 13.36 percent TWL & 1.94 percent CVCM. Only testing 

was done under vacuum. 

13. Loctite® appears to be sensitive to application process. What process verification test 

does Loctite® recommend for a given flight fastener? 

A13. I don't have information on flight fastener conditions. I don't know if Barry Sadler, our 

Boeing rep, could better answer this. He is in WA at 800 323-5106, hit choice # 1 and enter 

mailbox # 6118 when prompted. 

14. Can you provide any information concerning storage life in addition to that listed on the 

products? What is the shelf life of an open container? Does the size of the original container or 

residual amount of unused Loctite® effect shelf life? Are “single use packages” available and, if 

so, what are the advantages of this packaging compared to standard size packaging? 

A14. We do not specify shelf life after product is opened. These are very stable products and 

they're generally stored at room temperature in a cool, dry location. I have seen product opened 

years previous and there was no noticeable difference in appearance, cure rate, strength, etc. The 

key is to avoid contamination issues (i.e. touching the bottle tip directly down on a metal surface 

& sucking metal ions into the bottle that can lead to premature cure/hardening in the bottle). 

15. Loctite® 271 (Grade AV, red color) requires heat for disassembly. How much heat is 

required? 

A15. Disassembly is 450 ̊F temperatures and remove at temperature for both 271 & AV (these 

are two different products). 
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16. Do you recommend different fastener sizes for Loctite® 271, Loctite® 242, and Loctite®

2440? If so, what is the size range recommended for each product? 

A16. The attached table answers your question about typical bolt treating range. 

17. What is the use temperature range for Loctite® 242, Loctite® 2440, and Loctite® 271? 

Describe the data used to determine the use temperature ranges for these products. 

A17. We generally state a range of -65 ̊F - 300 ̊F. However, the most accurate answer to this 

question is to view the Hot Strength & Heat Aging graphs presented on the TDS's. These more 

closely mimic sustained high temperature & thermal cycling conditions. Anaerobics in general 

cover this broad temperature range, but every application is different and the performance at said 

temperature will vary from one product to the next and one application to the next, taking into 

consideration all application parameters. 

ANSWERS TO THESE QUESTIONS WERE PROVIDED (on Sept 8, 2006) ) BY: 

Michael Smigel 

North American Engineering Center Henkel/Loctite® Adhesives Rocky Hill, CT USA 

 
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1) Q: In Military specification MIL-S 45163A, the primer activator "Grade F" is called out. 

Although I haven't found grade F primer on the Loctite® website, I have found grade NF (called 

primer # 736). 

Is there a primer activator grade F? What are the differences/advantages of grade F and/or grade 

NF(#736) compared with #7471 (grade T) and #7649 (grade N)? 

A-1: the old, discontinued version of Loquic Primer N, product 764, met the requirements of 

MIL-S-46163 A Grade F. However, we never tested and certified this to the specification. 

This contained 1,1,1 trichloroethane and we took this off the market in 6/95. This was 

replaced by Locquic Primer N, product 7649. This latter alternative simply has a different 

carrier solvent, acetone. Otherwise, the function is the same. 7649 is also not tested and 

certified to the spec although it generally meets the requirements. 7649 is tested to MIL-S22473E Grade N Form R for existing designs and primers meeting this mil spec can be used 

with the adhesive/sealants that meet MIL-S-46163A. Locquic Primer NF, product 736, is 

not tested & certified to any mil specs. This is essentially a faster version of Loquic Primer 

N, 7649 and will provide faster fixturing with some of the machinery adhesives. Often 

Locquic Primer N & T are used interchangeably, with the only major difference being there 

on part life after drying on a part, prior to assembly. N is one month and T is one week. NF 

has a 30 minute maximum on part life. 

2) Q: In the Loctite® specs for 242, instructions indicate application of Loctite® to bolt only for 

thru holes, but recommends application of Loctite® to both male and female threads for blind 

holes. Why the difference? 

A-2: We recommend applying threadlocker to both male & female threads for blind holes to 

ensure uniform coverage of the threadlocker around the diameter and to ensure proper cure. If 

the threadlocker is just applied to the male threads and you torque this down, air pressure will 

force too much of the product out as you torque it down. The result is insufficient coverage 

around the threads and the product will start to cure/cross link, but it never fully cures. As a 

result, you experience premature failures. If applied to both parts for blind holes, this will 

compensate enough for squeeze out as you torque the assembly down. Often, if the product is 

applied incorrectly for blind holes, the failed assembly will have the appearance of a white, 

plastic ground up film with residual purple, blue or red color (depending on the product used) 

mixed in with it. This shows that it started to cure, but never fully cured. If properly applied, 

assemblies should have the appearance of a white, plastic ground up film exclusively, on the 

threads, once disassembled. There would be no residual of the original color mixed in. For thru 

holes assemblies, such as a nut and bolt combination, you simply apply the threadlocker to the 

male threads only and assemble. 
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ANSWERS TO THESE QUESTIONS WERE PROVIDED (on Nov 16, 2006) BY: 

Michael Smigel 

North American Engineering Center 

Henkel/Loctite® Adhesives 

Rocky Hill CT USA 

Q1. After removing fasteners that were coated with Loctite®, we have noticed a difference in the 

residual Loctite®/thread appearance for different products and wonder if this is an indication of 

different threadlocking mechanisms at work. Can Loctite® confirm that threadlockers (Product 

242 and 271) with primer/activator on stainless steel fasteners provide locking primarily or 

effectively by filling voids between the threads and damp vibration or do these products provide 

locking by bonding with the stainless steel threads (an adhesive effect)? Are there data to 

support the effects or relative contributions of the different locking mechanisms? 

A1. Brian, in essence the threadlockers perform both functions filling the voids and also 

providing adhesion to the metal. I'm not sure I understand what you're asking in your last 

question. What supporting data we have is typically representing on said TDS's. 

ANSWERS TO THIS QUESTION WAS PROVIDED (on Jan 26, 2007) BY: 

Michael Smigel 

North American Engineering Center 

Henkel/Loctite® Adhesives 

Rocky Hill CT USA 

 
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Appendix C. Evaluation of Anaerobic Locking Compounds, Tensile 

Testing, Torque Tension Testing, and Breakloose and Running 

Torque Testing 

Updated January 18, 2006 

C.0 INTRODUCTION 

The purpose of this test is to develop data on the effects of process variability that are likely to be 

encountered in using anaerobic threadlockers on ISS hardware. The data are intended to 

contribute to the understanding of the root cause of past failures and to be a guide for evaluating 

standards and processes for the use and application of Anaerobic threadlockers on ISS hardware. 

This testing will address mainly cure issues and fastener design parameters. 

C.1 Test Justification 

A number of ISS hardware components use anaerobic locking compounds as a means of meeting 

the redundant locking feature requirement for fasteners. Recently, the reliability of Anaerobic 

locking compounds has been brought into question due to a number of failures during ground 

testing. Failures have been related to a lack of proper procedures being followed for Anaerobic 

locking compound application, leading to incomplete curing. 

C.2 TEST OBJECTIVES 

A. Obtain typical load extension curves for fasteners and determine Johnson's 2/3rd's yield load 

values for the fasteners. 

B. Determine torque-tension relationships for various fastener/substrate combinations using 

anaerobic locking compounds and determine friction (k) factors. 

C. Evaluate level of adhesion and cure of anaerobic locking compounds results by conducting 

break loose and running torque tests on fastener/substrate/locking compound combinations and 

by conducting microscopic inspections of disassembled test specimens. 

C.3 APPLICABLE DOCUMENTS 

Document Title 

MSFC-STD-486 Standard, Threaded Fasteners, Torque Limits For 

EM10-OWI-MET-021 Torque Tension Testing of Metallic Fastening Systems 

NAS1352N08-16 Screw, Cap, Socket Head, Undrilled and Drilled, Plain and Self 

Locking, Alloy Steel and Corrosion resisting Steel, UNRC-3A 

NASM122119 Insert, CRES Helical Coil Coarse Thread, 1-1/2 Dia Nominal Length 

AN960-08 Washer, Flat 

NAS1004-8A Bolt - Machine, Hexagon Head, Non Magnetic, & Heat Resistant 
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Document Title 

NASM124696 Insert, CRES Helical Coil Fine Thread, 1-1/2 Dia Nominal Length 

NAS1587-4C Washer, Plain and Countersunk, 1200°F 

MS51831CA202L Insert, Screw-Thread, Locked In, Key-Locked, Heavy Duty 

NAS1958 Bolt, Shear, Hexagon Head 108ksi Shear, Long Thread 

NASM124700 Insert, CRES Helical Coil Fine Thread, 1-1/2 Dia Nominal Length 

NAS1587-8C Washer, Plain and Countersunk, 1200°F 

Loctite® 242 Anaerobic locking compound 

Loctite® 271 Anaerobic locking compound 

NASM1312-8 Fastener Test Methods, Method 8, Tensile Test 

NAS1069 Tension Fatigue Test Procedure For Aeronautical Fasteners 

C.4 TEST DESCRIPTION 

Load-extension curves will be developed for NAS1352N08-16, NAS1004-8A, and NAS1958-32 

fasteners. Johnson's 2/3rd's yield load values will be determined for each fastener type using 

NASM1312-8 test procedures. Johnson’s 2/3rd's yield load values will be used to determine 

load levels for torque-tension testing. 

Torque-tension curves will be developed for various fastener/substrate/locking compound 

combinations to establish torque values to use for locking compound level of adhesion and cure 

of anaerobic locking compound evaluations. Loctite® 242 will be used for 0.164" diameter and 

0.250" diameter fasteners. Loctite® 271 will be used for 0.500" diameter fasteners. 

Break loose and running torque tests will be conducted to evaluate level of adhesion and cure of 

anaerobic locking compounds. Microscopic inspections and photography will be performed to 

support these evaluations. 

C.4.1 Test Article Description 

C.4.1.1 Fastener tensile testing will be performed using a standard mechanical testing load 

frame and a NAS 1069 clevis (see enclosed picture). Three fasteners of each size - 0.164-32, 

0.2500-28, and 0.5000-20, shall be tested. 
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 C.4.1.2 Torque-tension testing will be performed in accordance with MSFC-STD-486 and 

EM10-OWI-MET-021 procedures using an SPS torque-tension testing machine capable of 

recording the induced load on the sample while simultaneously measuring the applied torque. 

Torque transducers of an appropriate torque range will be used to torque fasteners. Load cells of 

an appropriate load range will be used to record load during testing. Fasteners will be torqued 

from the head. Fasteners will be torqued into specimens containing either non-locking helical 

inserts, locking inserts, or tapped holes. An overview photograph of the torque-tension machine 

is shown below along with photographs showing typical tooling/fixtures for torquing the 

fasteners. 

 
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 A typical torque-tension testing test block is shown below. 

 

C.4.1.3 Break loose and running torque testing will be performed by torquing fasteners through 

spacers into test plates. A typical test plate and a typical test plate spacer are shown below. 

Fasteners shall be torqued as follows: row 1 to 100% torque (inch-pound) levels, row 2 to 75% 

torque levels, row 3 to 50% torque levels, and row 4 to 20% torque levels. Eight fasteners in 

each row shall be torqued with anaerobic locking compounds applied to the fastener threads. 

One of the eight fasteners in each row shall be installed through a load washer plus a spacer into 

test plates. Three fasteners in each row shall be used as control samples and torqued without 

locking compounds. 

 

SHEET 1 OF 1

NOTES: 1. BREAK SHARP EDGES

 MATERIAL: 2219- T87 OR - T851

3. UNLESS SPECIFIED 125

 VIBRO ETCH I.D. AT LOCATION

 SHOWN ON ONE SIDE OF BLOCK

5. CHEM FILM PER MIL- C- 5541 CLASS 1A

2

 .XX = +/- .01 ANGLES:

.XXX = +/- .005 +/- .5°

DATE: 09 - 20 - 2005

2

DRAWING NO: EM10- FX- 2121 REV A

MATERIAL:

UNLESS OTHERWISE SPECIFIED

MECHANICAL

METALLURGY

LOCTITE VIBRATION

.2 5 KEENSERT BLOCK

1.125

INSERT MS51831 CA - 202L

INSTALL PER MS51835

DO NOT BREAK THRU

.750

1.125

.563

.563

4

4

.2 50- 28 INSERT PLATE

09 - 20 - 2005

EM10 - FX- 2 116

.0 2

.0 10 ± .5° 1 1

- NOTES : 1. BREAK SHARP EDGES

 MATERIAL: 60 61- T6 , 22 19 - T87 OR 22 19 -T85 1

3.. UNLESS SPECIFIED 125

 INSERT NASM 12 46 96 (.2 50 -28)

 INSTALL PER NASM33 53 7

6. CHEM FILM PER MIL-C- 5 541 CLASS 1A

2

5.75

14.50

.50 1 .000

1.000

1.250

TYP

1.250

TYP

44X 4 44X 5

5

4

r .005

2 1

A

B

C

D

2 1

A

B

C

D

EM10

MECHANICAL

METALLURGY

 DATE:

 MATERIAL: 2

SHEET OF

 DRAWING NO: REV

UNLESS OTHERWISE SPECIFIED

.XX = ±

.XXX = ±

ANGLES
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C.4.2 Bolt Marking 

Fasteners of nominal diameter 0.1640-32 will be identified by bagging and tagging in plastic 

bags and numbering the bags from 1 - 44. Fasteners of nominal diameter 0.2500-28 will be 

identified by bagging and tagging in plastic bags and numbering the bags from 1 - 440. 

Fasteners of nominal diameter 0.5000-20 will be identified by bagging and tagging in plastic 

bags and numbering the bags from 1-88. 

C.4.3 Torque-Tension Testing Test Block Marking 

Torque-tension test blocks shall be labeled as indicated in table 1. 

Table 1: Torque-Tension Test Block Identification Labels 

Appendix 2: Test 

Configuration 

Size Substrate Insert/Hole Lubricant Test Block ID 

1 .2500-28 2219-T87 or T851 NASM124696, 1.5D Loctite® 242 25-1 to 25-5 

1 .2500-28 2219-T87 or T851 NASM124696, 1.5D Braycote® 601 25-6 to 25-10 

5 .1640-32 2219-T87 or T851 NASM122119, 1.5D Loctite® 242 16-1 to 16-5 

5 .1640-32 2219-T87 or T851 NASM122119, 1.5D Braycote® 601 16-6 to 16-10 

9 .5000-20 2219-T87 or T851 NASM124700, 1.5D Loctite® 271 50-1 to 50-5 

9 .5000-20 2219-T87 or T851 NASM124700, 1.5D Braycote® 601 50-6 to 50-10 

17 .2500-28 A286 H2 class 3 tapped hole, 

1.5D 

Loctite® 242 25H2-1 to 25H2-5 

17 .2500-28 A286 H2 class 3 tapped hole, 

1.5D 

Braycote® 601 25H2-6 to 25H2-10 

21 .2500-28 A286 H4 class 3 tapped hole, 

1.5D 

Loctite® 242 25H4-1 to 25H4-5 

21 .2500-28 A286 H4 class 3 tapped hole, 

1.5D 

Braycote® 601 25H4-6 to 25H4-10 

33 .5000-20 A286 H4 class 3 tapped hole, 

1.5D 

Loctite® 271 50H4-1 to 50H4-5 

.164-32 LOCTITE SPACERS

09 - 22 - 2005

EM10-FX-2128

.02

.010 ± .5° 1 1

- NOTES: 1. BREAK SHARP EDGES

 MATERIAL: 4340

3.. UNLESS SPECIFIED 125

4. HEAT TREAT TO ACHIEVE 40-45 HRC

5. ALL DIAMETERS TO BE CONCENTRIC WITHIN .005

2

.690 u.005

O .375

O .174 u.008

n .005 A

-Ai .002 A

2 1

A

B

C

D

2 1

A

B

C

D

EM10 MECHANICAL

METALLURGY

 DATE:

 MATERIAL: 2

SHEET OF

 DRAWING NO: REV

UNLESS OTHERWISE SPECIFIED

.XX = ±

.XXX = ±

ANGLES
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Table 1: Torque-Tension Test Block Identification Labels 

Appendix 2: Test 

Configuration 

Size Substrate Insert/Hole Lubricant Test Block ID 

33 .5000-20 A286 H4 class 3 tapped hole, 

1.5D 

Braycote® 601 50H4-6 to 50H4-10 

37 .2500-28 2219-T87 or T851 MS51831CA202L Loctite® 242 25K-1 to 25K-5 

37 .2500-28 2219-T87 or T851 MS51831CA202L Braycote® 601 25K-6 to 25K-10 

C.4 Break loose and Running Torque Test Plate Marking 

Break loose and running torque test plates shall be marked as shown in table 2. 

Table 2: Break Loose/Running Torque Test Plate Identification Labels 

Size Substrate Insert/Hole Test Plate ID’s 

.1640-32 2219-T87 or T851 NASM122119, 1.5D, thru 16TP-1 

.2500-28 2219-T87 or T851 NASM124696, 1.5D, thru 25TP-1 

.2500-28 2219-T87 or T851 NASM124696, 1.5D, blind 25TP-2 

.2500-28 A286 H2 class 3 tapped hole, 1.5D, thru 25TP-3 

.2500-28 A286 H4 class 3 tapped hole, 1.5D, thru 25TP-4 

.2500-28 A286 H4 class 3 tapped hole, 1.5D, blind 25TP-5 

.2500-28 2219-T87 or T851 MS51831CA202L, thru 25TP-6 

.2500-28 2219-T87 or T851 NASM124696, 1.5D, thru 25TP-7 

.2500-28 2219-T87 or T851 NASM124696, 1.5D, thru 25TP-8 

.2500-28 2219-T87 or T851 NASM124696, 1.5D, thru 25TP-9 

.2500-28 2219-T87 or T851 NASM124696, 1.5D, thru 25TP-10 

.5000-20 2219-T87 or T851 NASM124700, 1.5D, thru 50TP-1 

.5000-20 A286 H4 class 3 tapped hole, 1.5D, blind 50TP-2 

C.5 Instrumentation 

The instrumentation required to conduct the tests are inherent to the test facility. Measuring/test 

equipment with traceable calibrations to the National Institute of Standards and technology will 

be used to support these tests. The calibration system requirements will be per ANSI/NCSL 

Z540-1-1994. All test instruments will be operationally verified before each test and as required 

by the operating limits of the test. 

C.6 Photography 

Photographic coverage must document the pretest, test, and post-test inspections and conditions. 

Coverage is also required to illustrate test sample configurations, test performance, and anomaly 

and failure modes. Digital photographs of the test item and instrumentation will be taken as 

appropriate and necessary to adequately document pre-test tooling/fixturing, test setup, and test 

instrumentation. Each photograph will be labeled to identify its contents. 
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C.7 Test Data Requirements 

The following data will be required for this testing. 

C.7.1 Tensile Testing 

Fastener Part Number and ID number 

Fastener Diameter 

Measurement instrument calibration information 

Load-extension curves 

Johnson’s 2/3rd’s yield load values 

C.7.2 Torque-Tension Testing 

Torque transducer calibration information 

Load cell calibration information 

Test block ID number 

Fastener Part Number and ID number 

Anaerobic Type 

Torque-Load diagram 

C.7.3 Break loose and Running Torque Testing 

Torque transducer calibration information 

Load washer calibration information 

Test plate ID number 

Test hole number 

Torque level (100%, 75%, etc.) 

Anaerobic Type 

Installation time and date 

Cure time 

Disassembly time and date 

Break loose torque each hole 

Running torque each hole 

 
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C.8 Testing 

C.8.1 Tensile Testing 

Tensile testing will be conducted to determine load-extension curves for fasteners. Three 

fasteners of each part number NAS1352N08-16 (0.164-32), NAS1004-8A (0.250-28), and 

NAS1958C-32 (0.500-20) shall be tested. The tests will be conducted per the following 

procedures: 

1. Install test fastener into test fixture. 

2. Apply tensile load to failure, develop data specified in section 7.0. 

3. Repeat for 9 fasteners; 3 fasteners of each size. 

C.8.2 Torque-tension Testing 

Torque-tension curves will be developed for the configurations specified in table 1. The tests 

will be conducted using EM10-OWI-MET-021 and the following: 

1. Set up SPS torque-tension machine for the size fastener to be tested. 

2. Sample preparation: Clean the fastener threads with MEK. 

3. Install countersunk washer onto the fastener with the beveled side toward the fastener. 

4. Apply activator to the fastener threads for those test configurations for which it is specified. 

Let the activator dry for a minimum of 15 minutes. 

5. Apply anaerobic locking compound to the threads of the fastener to be tested using the droplet 

method. Use three drops applied every 120 degrees around the circumference of the fastener at 

the center of the threaded portion of the fastener, for all sizes of fasteners. Remove excess 

locking compound from the threads by tapping. 

6. Install the fastener through the torque fixture and screw hand tight into the substrate test block 

to be tested. 

7. Torque the fastener from the head using load control to the value specified in table 3. 

8. Unload to zero and repeat 5 cycles. 

 Table 3: Torque-Tension Testing Test Parameters 

Fastener No. Size Test Block ID Test Load (lbs) Torque Transducer 

Limit (in-lbs) 

Number of 

Cycles 

1 0.2500-28 25-1 3500 50 ft-lbs 5 

2 0.2500-28 25-2 3500 50 ft-lbs 5 

3 0.2500-28 25-3 3500 50 ft-lbs 5 

4 0.2500-28 25-4 3500 50 ft-lbs 5 

5 0.2500-28 25-5 3500 50 ft-lbs 5 

6 0.2500-28 25-6 3500 50 ft-lbs 5 

7 0.2500-28 25-7 3500 50 ft-lbs 5 

8 0.2500-28 25-8 3500 50 ft-lbs 5 

9 0.2500-28 25-9 3500 50 ft-lbs 5 

10 0.2500-28 25-10 3500 50 ft-lbs 5 
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Table 3: Torque-Tension Testing Test Parameters 

Fastener No. Size Test Block ID Test Load (lbs) Torque Transducer 

Limit (in-lbs) 

Number of 

Cycles 

11 0.2500-28 25H2-1 3500 50 ft-lbs 5 

12 0.2500-28 25H2-2 3500 50 ft-lbs 5 

13 0.2500-28 25H2-3 3500 50 ft-lbs 5 

14 0.2500-28 25H2-4 3500 50 ft-lbs 5 

15 0.2500-28 25H2-5 3500 50 ft-lbs 5 

16 0.2500-28 25H2-6 3500 50 ft-lbs 5 

17 0.2500-28 25H2-7 3500 50 ft-lbs 5 

18 0.2500-28 25H2-8 3500 50 ft-lbs 5 

19 0.2500-28 25H2-9 3500 50 ft-lbs 5 

20 0.2500-28 25H2-10 3500 50 ft-lbs 5 

21 0.2500-28 25H4-1 3500 50 ft-lbs 5 

22 0.2500-28 25H4-2 3500 50 ft-lbs 5 

23 0.2500-28 25H4-3 3500 50 ft-lbs 5 

24 0.2500-28 25H4-4 3500 50 ft-lbs 5 

25 0.2500-28 25H4-5 3500 50 ft-lbs 5 

26 0.2500-28 25H4-6 3500 50 ft-lbs 5 

27 0.2500-28 25H4-7 3500 50 ft-lbs 5 

28 0.2500-28 25H4-8 3500 50 ft-lbs 5 

29 0.2500-28 25H4-9 3500 50 ft-lbs 5 

30 0.2500-28 25H4-10 3500 50 ft-lbs 5 

31 0.2500-28 25K-1 3500 50 ft-lbs 5 

32 0.2500-28 25K-2 3500 50 ft-lbs 5 

33 0.2500-28 25K-3 3500 50 ft-lbs 5 

34 0.2500-28 25K-4 3500 50 ft-lbs 5 

35 0.2500-28 25K-5 3500 50 ft-lbs 5 

36 0.2500-28 25K-6 3500 50 ft-lbs 5 

37 0.2500-28 25K-7 3500 50 ft-lbs 5 

38 0.2500-28 25K-8 3500 50 ft-lbs 5 

39 0.2500-28 25K-9 3500 50 ft-lbs 5 

40 0.2500-28 25K-10 3500 50 ft-lbs 5 

1 0.1640-32 16-1 1500 200 in-lbs 5 

2 0.1640-32 16-2 1500 200 in-lbs 5 

3 0.1640-32 16-3 1500 200 in-lbs 5 

4 0.1640-32 16-4 1500 200 in-lbs 5 

5 0.1640-32 16-5 1500 200 in-lbs 5 

6 0.1640-32 16-6 1500 200 in-lbs 5 

7 0.1640-32 16-7 1500 200 in-lbs 5 

8 0.1640-32 16-8 1500 200 in-lbs 5 

9 0.1640-32 16-9 1500 200 in-lbs 5 

10 0.1640-32 16-10 1500 200 in-lbs 5 

1 0.5000-20 50-1 26000 5 

2 0.5000-20 50-2 26000 5 

3 0.5000-20 50-3 26000 5 

4 0.5000-20 50-4 26000 5 

5 0.5000-20 50-5 26000 5 

6 0.5000-20 50-6 26000 5 

7 0.5000-20 50-7 26000 5 

8 0.5000-20 50-8 26000 5 

9 0.5000-20 50-9 26000 5 

10 0.5000-20 50-10 26000 5 

11 0.5000-20 50H4-1 26000 5 

12 0.5000-20 50H4-2 26000 5 

13 0.5000-20 50H4-3 26000 5 

14 0.5000-20 50H4-4 26000 5 

15 0.5000-20 50H4-5 26000 5 

16 0.5000-20 50H4-6 26000 5 

17 0.5000-20 50H4-7 26000 5 

18 0.5000-20 50H4-8 26000 5 

19 0.5000-20 50H4-9 26000 5 

20 0.5000-20 50H4-10 26000 5 
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C.8.3 Breakloose and Running Torque Testing 

Breakloose and running torque testing will be conducted according to the following procedure: 

1. Sample preparation: Clean the fastener threads with MEK. 

2. Install countersunk washer onto the fastener with the beveled side toward the fastener. 

3. Apply activator to the fastener threads for those test configurations for which it is specified. 

Let the activator dry for a minimum of 15 minutes. 

4. Apply anaerobic locking compound to the threads of the fastener to be tested using the droplet 

method. Use three drops applied every 120 degrees around the circumference of the fastener at 

the center of the threaded portion of the fastener, for all sizes of fasteners. Remove excess 

locking compound from the threads by tapping. 

5. Install fasteners to the torque values specified in table 4. One fastener in each row will be 

installed with a load washer to determine load level versus torque. 

6. Let the locking compound cure for a minimum of 30 hours. 

7. Remove the fasteners from the test plate. 

8. Record the information specified in section 7.0. 

9. Bag and tag all fasteners for subsequent inspection. 

10. Microscopic inspection and photography of fasteners as appropriate and necessary. 

 

Table 4: Break Loose/Running Torque Test - Installation Torque Levels 

Torque Level (in-lbs) 

 Row 1 (100%) Row 2 (75%) Row 3 (50%) Row 4 (25%) 

Test Plate ID Col 1-8 Col 9-

11 

 Col 1-8 Col 9-

11 

 Col 1-8 Col 9-

11 

 Col 1-8 Col 9-11 

16TP-1 52 42 39 32 24 20 13 10 

25TP-1 297 266 225 200 150 138 78 69 

25TP-2 297 266 225 200 150 138 78 69 

25TP-3 287 287 220 220 153 153 80 80 

25TP-4 301 302 234 230 162 162 82 84 

25TP-5 301 302 234 230 162 162 82 84 

25TP-6 200 185 140 150 90 110 50 65 

25TP-7 297 266 225 200 150 138 78 69 

25TP-8 297 266 225 200 150 138 78 69 

25TP-9 297 266 225 220 150 138 78 69 

25TP-10 297 266 225 200 150 138 78 69 

50TP-1 

50TP-2 

 
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C.8.4 Post Test 

Post test operations on each bolt may begin after each bolt is tested. A post-test visual and 

microscopic inspection is required for each break loose and running torque test. All post-test 

anomalies will be reported and documented. 

C.9 Reports 

A final report will be written upon completion of all testing. Anomalies and objectives will be 

addressed and test results shall be fully documented in the report. 
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Appendix D. CTE Effects of Fastener Mechanical Loads 

To request the data information, please go to URL: 

http://www.nasa.gov/offices/nesc/home/index.html
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Appendix E. NASM1312-7 Vibration Testing Test Plan 

This document was purposely left marked as Draft. 
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Appendix F. Comparison of Secondary Locking Features for 

Threaded Inserts, July 2007 

The author of this document served as a team member on this 

NESC assessment under contract number NNL07AA00B. 
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Appendix G. Thermal Vacuum Testing and Results 

This work was conducted by NASA Personnel for the NESC. 

To request the data information, please go to URL: 

http://www.nasa.gov/offices/nesc/home/index.html
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Appendix H. Human Factors Review of Application Process for 

Liquid Locking Compounds (LLC) in ISS Hardware 

Loctite® is an LLC, although there are other brands of LLC’s. “LLC” and the trade name 

“Loctite®” are used interchangeably. The three standards below were reviewed and 

inconsistencies/incongruities among the standards assessed, including descriptions of 

activators/primers, cure time and the activator/primers, activator/primers and inactive metals, and 

the application of LLCs on fastening hardware. Current information obtained from the Loctite®

manufacturer regarding certain application features was also assessed. 

H.1 Relevant Standards Documents 

MIL-S-22473E “Military Specification: Sealing, Locking, and Retaining Compounds: (Single 

Component)” (dated 12 Apr 1983, and cancelled 21 Jan 2004) lists and specifies 15 separate 

compound GRADES (listed as letters from AA to JV) based on viscosity and locking torque. 

MIL-S-22473E does NOT cover any of the liquid locking compounds used in the tests conducted 

by this NESC (i.e., Loctite® 222, 242, and 271). This Mil Spec’s Table I lists “locking torque” 

(not further defined) standards for the 15 compounds for a 3/8” x 24TPI plain steel bolt. 

MIL-S-22473E also specifies two grades of “surface primers and cleaners” (grades “N” and 

“T”). MIL-S-22473E alludes to primer’s activating function on inactive metals in the following 

statements (although the terms “activation” or “activator” are not used): Either surface primer 

grade specified in this Mil Spec, “...when applied to unpolished and untreated cadmium or zinc 

surfaces [assume this means any passivated or inactive metal surface], shall cause 

polymerization...” [of the 15 sealant grades]. However MIL-S-22473E does NOT mention 

stainless steel or titanium as inactive metals suitable for use with liquid locking compounds. 

MIL-S-22473E describes the “surface primer/cleaners” Grade “N” and Grade “T,” which 

includes (Loctite® 7471, or grade “T”) used in the tests conducted by the NESC. 

MIL-S-22473E (section 4.6.2.1.1) describes the application of liquid locking compound, in 

performing the QA tests, as follows: “...sufficient compound shall be applied by means of the 

application nozzle supplied with the product to cover completely the protruding threads of the 

bolt.” No mention is made of whether the LLC is applied to male threads, female threads, or to 

both. 

MIL-S-46163A “Military Specification: Sealing, Lubricating and Wicking Compounds: 

Thread-Locking, Anaerobic, Single-Component” (dated 12 Jul 1983, and inactivated for new 

design 23 Mar 2001) specifies three separate types of compounds, each containing three 

separate compound GRADES, for a total of nine compounds. The three types are I, Sealing type 

(standard viscosity); type II, Lubricating type (thixotropic -- which thin when subjected to strains 

greater than the yield strain and regain thickness after rest); and type III, and Wicking type (fast 

curing, low viscosity). None of the nine compound letter grades specified in MIL-S-46163A 
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appeared in MIL-S-22473E. MIL-S-46163A Table II specifies viscosity of the nine compounds. 

In Table II there are comparable viscosities to those listed in MIL-S-22473E Table I for only 

three of the nine compounds. Also the locking torque standards specified in MIL-S-46163A 

Table III are not the same as the torque standards listed in MIL-S-22473E Table I. It is clear that 

the two MIL Specs are dealing with different types of liquid locking compounds. There is NO 

overlap in the LLCs described in MIL-S-22473E and MIL-S 46163A, nor is there redundancy in 

the primer/activators described in the two MIL Specs. 

MIL-S 46163A is very specific in referring to LLCs for thread-locking. Section 6.1 describes 

these compounds as “...liquid and in use, are converted to an infusible, insoluble state by 

confinement between closely fitting metal surfaces (under anaerobic conditions).” Further, they 

are “...designed to lock threaded assemblies against working loose under shock and vibration.” 

That section describes the three “types” of LLC as follows: “Type I compounds are intended for 

use in sealing threaded fasteners, plugs, and other threaded fittings against fluid pressure. Type 

II compounds (having excellent lubricity) allow a minimum of metal to metal friction, thus 

reducing galling on the thread flanks. Type III compounds, which have a low viscosity, are 

intended for use in closely fitting joints or for application to the outside of an assembled joint 

into which the compound flow by capillary action and cures.” 

MIL-S 46163A introduces “Prevailing Torque”, in addition to “Locking Torque”, as a metric for 

QA testing of liquid locking compounds. Table III lists both prevailing and locking torque 

values for plated-, as well as plain-steel 3/8” NC (16TPI) Grade 5 fasteners. Locking torque is 

stated to be ”breakaway torque” (otherwise undefined), while prevailing torque is defined as the 

average torque values at 1⁄4, 1⁄2, 3⁄4 and 1 full turn. 

MIL-S 46163A (section 1.2.2) specifies primer F as the surface primer-cleaner to be used with 

the nine compounds described in the document. MIL-S 46163A does not mention either of the 

primer grades, “N” or “T,” specified by MIL-S-22473E. MIL-S 46163A section 6.9.1 alludes to 

primer’s activating function with LLCs on inactive metals in the following statements (although 

the terms “activation” or “activator” are never used): “Primers for inert surfaces,” [i.e., grade F] 

are required for surfaces “such as zinc, cadmium, and gold platings” ... “in order to meet the 

curing rate requirement of 3.5.2.” Section 3.5.2 of MIL-S 46163A says, “The primer used in 

conjunction with Types I, II and III compounds on cadmium and zinc-plated surfaces shall be 

compatible to the compounds and shall provide a breakaway and prevailing torque of not less 

than 50 percent of the minimum specified in Table III after 15 minutes; and not less than 100 

percent of the minimum specified in Table III after 4 hours when tested as specified in 4.6.3.2.” 

MIL-S 46163A, section 4.6.3.2, states that the compound is to be applied “...to the threads of 

BOTH [emphasis added] the nut and bolt...” 

In correspondence with Henkel/Loctite® Company’s North American Engineering Center (Mike 

Smigel, Henkel/Loctite®, to Brian Jensen, NESC, 16 Nov 2006) we learned that primer Grade 

“F” was never tested and certified to MIL-S-46163A. Further, Primer Grade F was removed 
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from the market in June, 1995 and primer Grade N (Loctite® product number 7649) was 

recommended in its place. Further, Henkel/Loctite® has said that, “[primer N] 7649 is also not 

tested and certified to [MIL-S-46163A] although it generally meets the requirements. 7649 is 

tested to MIL-S-22473E Grade N Form R for existing designs and primers meeting this mil spec 

could be used with the adhesive/sealants that meet MIL-S-46163A.” Henkel/Loctite® continues, 

“Often Locquic Primer [grades] N [product 7649] & T [product 7471] are used interchangeably, 

with the only major difference being there on part life after drying on a part, prior to assembly. 

[Grade] N is one month and T is one week.” This information from Henkel/Loctite® Co. 

confirmed Primer N or Primer T could be used with the adhesive/sealants that meet MIL-S46163A. Thus Primer T (Loctite® product 7471), the activator used in the tests conducted by this 

NESC, meets the specifications of MIL-S-22473E and is compatible with the liquid locking 

compounds described in MIL-S-46163A. 

ASTM D5363-03 “Standard Specification for Anaerobic Single-Component Adhesives (AN)” 

(dated Dec. 2003, and corrected Aug 2006); states that it is intended to replace both MIL-S22473E and MIL-S-46163A. 

ASTM D5363-03 covers both the primer/activators mentioned in MIL-S-22473E including 

Grade “T” as used in the tests conducted by this NESC (It refers to them only as “primers” 

however), and it also covers both of the liquid locking compounds used in the tests conducted by 

this NESC. 

ASTM D5363-03 specifies three groups of anaerobic adhesives. Group 01 includes “slow 

curing” LLCs with “Newtonian flow properties (viscosity is constant over a range of strain 

rates). The Group 01 locking compounds are identical with those 15 compounds covered in 

MIL-S-22473E. Torque strength standards for group 01 LLCs were set using 3/8” UNF 24TPI 

Grade 2 bolts. The torque strength standards and viscosities between the two documents are 

exactly alike. Group 02 are fast curing LLCs with Newtonian flow properties – this group 

includes Loctite® product 271 (group 02, class 2, grade 1, color red). The Group 02 locking 

compounds are similar to LLCs of Type I (Grades J, K, L) and Type III (Grades P, Q, R) in MILS 46163A. Similar, but the torque strength standards and viscosities between the two documents 

are not the same (if often close). Group 03 are fast curing, lubricating LLCs with “thixotropic 

flow properties (they thin when subjected to strains greater than the yield strain and regain 

thickness after rest) – Loctite® product 242 is included in this group (group 03, class 2, grade 1, 

color blue). The Group 03 locking compounds are what is referred to in MIL-S 46163A as “Type 

II” LLCs (Grades M, N, O). Torque standards for both groups 02 and 03 LLCs were set using 

3/8” UNC 16TPI Grade 5 bolts. 

ASTM D5363-03 mentions Primers [sic] Grade N and T (but not Grade F). Like the two MILSpecs it replaces, this ASTM document mentions Aluminum Alloy 2024, Brass, Steel, and 

Plating, both Cadmium & Zinc; and also like them it does NOT mention stainless steel or 

titanium as materials for LLCs. 
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ASTM D5363-03 defines “...breakaway torque as the initial torque required to break the bond, 

measured at the first movement between the nut and the bolt, when unscrewing an unseated 

assembly.” Prevailing torque is defined as torque measured at 180° rotation of the nut. 

“However, for purposes of this specification, the definition of prevailing torque as the average of 

the four torques measured at 90, 180, 270, and 360° rotation of the nut is also acceptable.” 

ASTM D5363-03, sections 7.5.1.1-4, specifies LLC application as follows: “Screw the nut onto 

the bolt such that 0.5 to 0.5625 in. (12.7 to 14.3 mm) of the threaded end protrudes. Apply 

sufficient adhesive to the bolt to completely cover the protruding threads of the bolt. Unscrew 

the nut over the adhesive until the end of the nut is flush with the end of the bolt. 7.5.1.4 Screw 

the nut back until 0.125 to 0.1875 in. (3.2 to 4.8 mm) of threads protrude to ensure complete 

coverage of the adhesive in the engaged area.” Thus both male and female threads are coated 

with LLC, but it is applied only to the male thread. 

ASTM D5363-03 specifies “percent of strength” after cure for each of the primers N & T in the 

document’s Table 3. Primed zinc or cadmium plated (i.e., inactive metal) fasteners using Grade 

N (Loctite® 7649) primer, should yield prevailing torque of not less than 50 percent strength at 

standard conditions after 6 hours; and not less than 100 percent after 24 hours. Using Grade T 

(Loctite® 7471) primer on inactive metal, should yield strength at standard conditions of not less 

than 50 percent after 30 minutes; and not less than 100 percent after 2 hours, according to Table 

3. Strength at standard conditions, measured as both breakaway and prevailing torque, -- on 

plated or inactive metal, using Loctite® 271(group 02, class 2, grade 1, red LLC) -- is 16.9 - 39.5 

N-m (150 - 350 inch-pounds), and 4.5-56.5 N-m (40-500 inch-pounds), respectively. Using 

Loctite® 242 (group 03, class 2, grade 1, blue LLC) strength at standard conditions is 1.1 – 22.6 

N-m (10 - 200 inch-pounds), and 0.6-22.6 N-m (5-200 inch-pounds), respectively. 

H.2 Inconsistencies of describing Primer/Activator in Standards Documents 

These three main specification documents (MIL-S-22473E, MIL-S-46163A, & ASTM D5363-

03) for using primer/activators are mainly clear and complete. However, as shown below, there 

are some lapses and some conflicting directions/conclusions among the several specs, and 

between them and Henkel/Loctite® Co., a major LLC manufacturer. 

Cure Time and the Two Primer/Activators 

MIL-S-22473E specifies either surface primer Grade T (Primer, “Quick,” Yellow or Green, 

Loctite® product 7471) or surface primer Grade N (Primer, “Normal,” Green, Loctite® product 

7649) for MIL-S-22473 LLCs. MIL-S-22473E does not mention stainless steel or TITANIUM as 

materials for liquid locking compounds (LLCs). It does mention Aluminum Alloy 2024, Brass, 

Steel, as well as Zinc and Cadmium Plating. This document implied that primer could be used as 

a cleaner and will insure a cure on plated metals. However the impression is left that Grade T 

somehow affects a “quick” cure. 
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ASTM D5363-03 specifies prevailing torque for both primers N & T in the document’s Table 3. 

This document declares that “Primer T” is faster curing for inactive metal fasteners, “Primed 

zinc or cadmium plated (i.e., inactive metal) fasteners using Grade N (Loctite® 7649) primer, 

should yield prevailing torque of not less than 50 percent strength at standard conditions after 6 

hours; and not less than 100 percent after 24 hours. Using Grade T (Loctite® 7471) primer on 

inactive metal, should yield strength at standard conditions of not less than 50 percent after 30 

minutes; and not less than 100 percent after 2 hours, according to Table 3. Torque standards for 

groups 02 and 03 LLCs were set using 3/8” UNC 16TPI Grade 5 bolts. 

MIL-S-46163A specifies “Grade F Primer-Normal compound, green color;” for MIL-S46163 

LLCs. Its section 6.3 further specifies Grade F primer should be used when LLC is applied 

below 40°F. MIL-S46163 does NOT mention stainless steel or titanium as materials for LLCs. It 

does mention Aluminum Alloy 2024, Brass, Steel, and Plating, both Cadmium & Zinc. 

In NESC correspondence with Henkel/Loctite® USA, the company states that primer/activator T 

will not necessarily create a faster cure than activator N on inactive metals. The correspondence 

stated that the ONLY consistent difference between the two activators is the on-part shelf life (T 

is 7 days and N is 30 days). 

Primer/Activators and Inactive Metals 

NESC correspondence with Henkel/Loctite® USA revealed, “Primer’s function on inactive 

metals like stainless steel is different [from “active” metals] in the sense that it ensures full cure 

in 24 hours. If no primer is used on inactive metals like stainless, most of the threadlockers will 

take significantly longer to fully cure and the timeframe is highly unpredictable. It could take 2-

3 weeks to fully cure without a primer. The real question becomes ...when do you want to put 

the parts back in service? In further correspondence Henkel/Loctite® said, “One of the main 

functions of the primer [sic.] is to ensure full cure in 24 hours at room temperature. The primer 

puts a layer of metal ions down on the part to accelerate the cure on "inactive metals" which 

include some materials (e.g., stainless steel and titanium) and any protective coating such as in 

platings, anodized aluminum and galvanized steel. The threadlockers cure in the absence of air 

and metal ions are a catalyst in curing them. [Loquic] 7649 contains copper salt & [Loquic] 7471 

contains an amine and these serve that function. Further questions to Henkel/Loctite® regarding 

the LLCs behavior in stainless steel after full 24 hour cure is more ambiguous. When asked if 

Loctite® 242 or 271 actually bond (“adhere”) to the stainless steel threads or it the LLCs 

“cohere” when cured to fill the voids, but do not bond to the metal, the answer was, ”...in 

essence the threadlockers perform both functions, filling the voids and also providing adhesion to 

the metal.” But they would not venture an opinion on the relative contributions of the different 

locking mechanisms in this application. 

As noted, MIL-S 46163A specifies primer F as a surface primer-cleaner. MIL-S 46163A 

(section 6.9.1) describes that “Primers for inert surfaces,” (i.e., grade F) are REQUIRED 
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[emphasis added] for surfaces “such as zinc, cadmium, and gold platings” Correspondence with 

Henkel/Loctite® USA ascertained that Primer F has been replaced by Primer N, and further that 

Primers N and T may be used interchangeably to cause LLCs to cure within 24 hours on stainless 

steel fasteners. 

ASTM D5363-03 mentions “Primers” [sic] Grade N and T, but not Grade F. Like the two MIL-S 

it replaces, this ASTM document mentions Aluminum Alloy 2024, Brass, Steel, and Plated 

fasteners, both Cadmium & Zinc; and also like them it does NOT mention stainless steel or 

titanium as materials for LLCs, or to refer to the primers as “activators.” 

Application of LLC 

MIL-S 22473 is vague in its application instructions. MIL-S 46163A instructs the user to apply 

LLC to both nut and bolt. ASTM D5363-03 directs the user to apply LLC to the bolt only. 
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Appendix I. Loctite® Application Process Comparison 

This appendix describes aspects of the preparation and application of LLC’s for five ISS 

manufacturing sites. The standards listed below were reviewed relative to their use for the 

application of LLCs to flight hardware. The review included; (1) how activator/primer is 

described in the documents, (2) a comparison of the documents, (3) how LLC’s are described in 

the documents, and, (4) results of field observations of applying Loctite® during ISS rework 

operations. 

1. Boeing Document BAC 5011, “Application of Retaining Compounds” (Dec-86)

2. Boeing Document Dwg. 683-13000 “Hatch Assembly” (May, 2005)

3. Lockheed Martin (Michoud Oprs) Document STP 2009B, “Locking and Sealing 

Compounds, Application of” (Sep-04) 

4. Rockwell Document MA0106-333, “Application of Locking and Retaining Compound to 

Threaded Electrical, Hardware and Mechanical Fasteners” (Dec-85)

5. Boeing Huntington Beach Document MA0106-333, “Application of Locking and 

Retaining Compound to Threaded Electrical, Hardware and Mechanical Fasteners” (Apr04) 

How Primer/Activator is described in ISS Manufacturing Documents 

A sample of ISS contractors’ process and procedures documents for using primer/activators are 

mainly clear and complete. However there are some lapses and some conflicting 

directions/conclusions among the several contractors, and between them and Henkel/Loctite®

Co. 

Boeing Document BAC 5011, “Application of Retaining Compounds” (Dec-86) states: Use 

MIL-S-22473 Grade T primer for MIL-S-22473 compounds; and MIL-S-46163 Grade F 

primer/activators for MIL-S-46163 compounds. "Coat surface with Primer/Activator prior to 

application of locking compound." "Air dry primer/activator for 5 min minimum..." "Primed 

parts could be stored in poly bags up to 24 hours" [NOTE: Grade F primer/activator – Not 

produced or available for purchase -- is called for when using MIL-S-46163 LLCs, in this still 

current guidance document. Also note the use of the term “primer/activator” to denote the 

activation required for reliable cure of LLC on inactive metals 
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Boeing Document Dwg. 683-13000 “Hatch Assembly” (May, 2005). Although this document 

parallels BAC 5011, it represents a specific application of the guidance of the latter. This does 

not specifically mention “primer” or “cleaner” or “activator.” 

Lockheed Martin (Michoud Oprs) Document STP 2009B, “Locking and Sealing 

Compounds, Application of” (Sep-04), states, Grade T (quick) and N (normal)...surface primer 

activators (meeting curing rate specified in MIL-S-22473) are required for ...plated surfaces..., 

chemical conversion coat[ings], passivated surfaces..." "...primer shall completely coat the area 

to be coated by compound...shall completely cover the junction where the bolt threads protrude 

through the nut. [NOTE: different cure times for LLC prepared using primer/activators "T" and 

"N" are stated in Table V, (and labeled “Quick” and “Normal” respectively) -- but are NOT 

restricted to "active" metals only. This suggests that grade T primer/activator provides a quick 

cure in all applications]. 

Rockwell Document MA0106-333, “Application of Locking and Retaining Compound to 

Threaded Electrical, Hardware and Mechanical Fasteners” (Dec-85) states, MIL-S-22473 

Grade T primer [sic] shall be used with any MIL-S-22473 LLC in this document. "[Grade T] 

primer shall be omitted on titanium hardware." [NOTE: titanium fasteners are stated by 

Henkel/Loctite® to require activator to ensure LLC cure in 24 hours]. "Apply Grade T onto 

external and internal threads..." Clean up excess primer with cloth & Trichloroethane. Allow to 

dry 15 min minimum. May be kept 5 days in plastic bag. Curing the LLC is stated as, 

“Minimum 3 hours. May be handled after 30 min, but shall not be stressed until full cured.” 

[NOTE that this short cure time suggests grade T primer provides a quick cure on all materials]. 

Boeing Huntington Beach Document MA0106-333, “Application of Locking and Retaining 

Compound to Threaded Electrical, Hardware and Mechanical Fasteners” (Apr-04) [NOTE 

the document number is the same as the Rockwell document above, but is of much later date] 

states, Primers [sic] are used to cure LLC on inactive surfaces. Primer should be used on all 

surfaces to be treated with LLC. Primer N has an on-part life of 30 days. Primer T's on-part life 

is 7 days. Both primers result in equal strength bond. Apply primers to internal and external 

threads of fastening system, and prevent application on other surfaces. Apply a thin film, do not 

"puddle." Allow to dry for 15 min. [NOTE: Although it omits the term “activator,” this 

contractor’s description of the purpose and application of primers/activators N and T are 

otherwise consistent with what Henkel/Loctite® USA has described for LLCs on inactive 

metals]. Cleaning before LLC application is as follows, “Both internal and external threads of 

the fastening system shall be cleaned with acetone or MEK...” 
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I.2 Comparison among the Five Application Procedure Documents 

This comparison shows a variety of implied definitions of primers as cleaners, as cure 

accelerators, or as necessary for reliable cure on inactive metals in 24 hours. The five documents 

also call for differing and various types of LLCs without background or reasons for the choice. 

Differences in LLC cure times are also evident among the documents. There are three unique 

deviations in individual documents including statements that primer is not required before LLC 

application on titanium; that LLCs are not used on flight fasteners larger than 1/4” diameter; and 

that LLCs could be applied over dry film lubricant.

How LLC is described in ISS Manufacturing Documents 

Boeing Document BAC 5011, “Application of Retaining Compounds” (Dec-86) 

This document states: "Locking surfaces [note plural] shall be covered with retaining compound, 

as evidenced by a continuous fillet visible at the parting line of the assembled joint. Remove 

excess material." Cure LLC “...72 hours @ 40 ̊F to 70 ̊F. 1 hour @ 70 ̊F and above. "Do not 

subject joined parts to handling, vibration or shock until cured." [Note: The range in cure times 

does not coincide with Henkel/Loctite®’s opinion that LLC will achieve full cure in 24 hours on 

stainless steel if primer/activator is used first]. Cleaning materials or methods are not described. 

Boeing Document Dwg. 683-13000 “Hatch Assembly” (May, 2005) 

Although this document parallels BAC 5011, it represents a specific application of the guidance 

of the latter. This document incorporates specific language for the task as follows: "Thread lock 

adhesive shall be applied to jam nut/tension rod threads. (Ref BAC 5011 for Boeing internal 

use). Thread lock adhesive per MIL-S-22473, Grade HV, Brown, shall be used." [NOTE that in 

accordance with BAC 5011, the LLC is to be applied to the rod and nut threads, plural]. The 

LLCs are called out as follows: "... optional thread lock adhesive allowable: MIL-46163A Type 

II Grade M, (Loctite® 222MS, Preferred option), MIL-46163A, Type II Grade N (Loctite® 242), 

MIL-S-22473E, Grade AV (Rite-Lok TL-71) [red color, similar performance specifications to 

Loctite® 271], Loctite® 246." 

Lockheed Martin (Michoud Oprs) Document STP 2009B, “Locking and Sealing 

Compounds, Application of” (Sep-04), calls out the LLCs as follows: MIL-S-22473 Grades 

A,H,EV,C,AV,CV,E,AA,B,D,HV & Loctite® Grade 294 [wicking type, not referenced in MILS-22473]. Specific LLC application procedures are described only for Loctite® product 294 

(wicking type). "Using a clean wiping cloth wipe off excess compound after it has remained on 

the interface between the bolt and nut for a minimum of 24 hours." "If ... handled after 

application and before cure, they shall be handled in a manner so that there is no relative motion 

between mating surfaces. Cure time is specified as “2 hours cure with Primer T; 6 hours cure 

with Primer N, [NOTE that the use for inactive metals is not described]. Cleaning materials and 

methods are as follows, "Contamination and grease shall be removed...by vapor degreasing or 
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by use of [MEK]." "The applied compound shall be smooth, homogeneous, and free of lumps, 

abrasives, and other contamination." 

Rockwell Document MA0106-333, “Application of Locking and Retaining Compound to 

Threaded Electrical, Hardware and Mechanical Fasteners” (Dec-85) says that the LLCs are 

“...used as auxiliary retaining method for mechanical fasteners.” The document calls for MIL-S22473 Grades A (red 100-250 in lbs), C (blue 40-100 in lbs), N [sic] (brown, 10-25 in lb). 

[NOTE, Brown sealant is Grade "H." GRADE "N" IN 22473 REFERS TO "Normal" PRIMER]. 

Cleaning parts is stated as, "...shall be cleaned by solvent wiping per MA0110-303." (formerly 

called for Trichloroethane -- MEK for titanium -- per MA0110-303). LLC application procedure 

is stated as follows: "...applied to BOTH [emphasis added] mating threads by camel hair brush 

or by nozzle-equipped containers. Use only as much compound as is needed to fill the space 

between the mating surfaces. Remove excess compound by wiping with a clean cloth wet with 

trichloroethane." Do not coat adjacent areas, apply only to threads. Verification of torque value 

shall be completed within 5 min elapsed time from application. Curing is stated as, “Minimum 3 

hours. May be handled after 30 min, but shall not be stressed until full cured.” 

Boeing Huntington Beach Document MA0106-333, “Application of Locking and Retaining 

Compound to Threaded Electrical, Hardware and Mechanical Fasteners” (Apr-04) [As 

noted above, this document’s number is the same as the Rockwell document, but a much later 

date]. It describes cleaning before LLC application as follows, “Both internal and external 

threads of the fastening system shall be cleaned with acetone or MEK...” Regarding LLC, this 

document limits their use to “flight hardware of 1⁄4” diameter and smaller.” Further, "Usage is 

acceptable with ... moly disulfide dry film lubricant.” [NOTE: This use is in contrast with the 

Henkel/Loctite® opinion]. The document refers to "liquid locking compounds (LLC)." It calls 

out LLCs only from the following: MIL-S-22473 Grade A, Red, for 100-250 In.-Lb Torque with 

3/8-inch fastener; Grade C, Blue, 40-100 In.-Lb Torque with 3/8" fastener; Grade H, Brown, 10-

25-inch-lb torque with 3/8-inch fastener. Grade H used for 0.250 inch-0.190 inch fasteners; 

Grade JV used for 0.164 inch-0.112 inch diameter fasteners. The application procedure is quite 

detailed and consistent with Henkel/Loctite® guidance: "Sealant shall be applied to both internal 

and external thread, except when female is thru hole in FOD critical application. For 0.250 inch 

and smaller fasteners, two drops of sealant shall be applied 180 degrees apart. It will cover a 

minimum of 90 percent of the threads. Excess sealant is removed using acetone or MEK. 

Processes shall be qualified for each combination of materials used prior to acceptance of the 

first production part." The only mention of LLC curing were two statements, “Caution, LLC 

will cure in a vacuum” and “Final torque must be achieved within 5 minutes of application,” 

(which suggested LLCs will cure quickly). 
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I.3 Results of Field Observation 

A technician, who was applying Loctite® at one of NASA’s vendor facilities performing rework 

on the ISS, was observed as part of field work to provide information to the NESC. This 

technician’s supervising engineer verified that the technician had received classroom training 

before performing the rework operation using Loctite® on stainless steel fasteners. As requested, 

the technician performed a simulation of that portion of the rework operation, in which Loctite®

liquid locking compound was applied to a stainless steel 3/8 x 24 threads per inch bolt and nut 

assembly. The technician did not apply the primer/activator during this demonstration and, 

when questioned about this omission, the technician explained that acetone (a major ingredient in 

primer/activator 7471) was usually used in the rework operation to remove residual cured 

Loctite®. The technician assumed because the demonstration bolt and nut were new, that the use 

of the "cleaner/primer" was not required. The technician used Loctite® 242 (one of several 

approved LLCs) in the rework drawing. Although, the LLC was only applied to the threads on 

the sample bolt and not to the nut (per BAC 5011, and the rework drawing), the application on 

bolt only was consistent with the actual threaded part – on which the nut remained captive during 

the rework process. This observed demonstration was consistent with the effects of incomplete 

explanation/understanding of the real purpose of using primer/activator to cure the LLC (in a 

threaded fastener made from inactive metal). In addition, the possibly ambiguous instructions 

existed in the rework drawing, to apply LLC to nut/tension rod threads. 
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Appendix J. Literature Review of the Self-Locking of Threaded 

Fasteners 

J.1 Introduction 

This literature review provides an overview on the self-loosening of threaded fasteners, which 

specifically includes bolted joints. Initially, a brief chronological overview of research reports 

related to the self-loosening of fasteners due to vibration is provided. Then a summary of 

parameters that have been identified by the authors of the research articles are summarized and 

followed by a section which presents a brief overview of some testing machines that have been 

used. This literature review is organized to be only a review of the topic, and details on any of 

the testing and research that was conducted may be found in the original articles that are 

identified in the reference section. 

J.2 Overview 

Threaded fasteners have been in use by designers and engineers for many years. The reason is 

that they provide a simple and proven solution for assembling multiple parts together in an 

efficient and effective manner.4

 Creating a one-piece structure capable of providing the same 

functionality as a given assembly would be impossible in some cases, as well as impractical in 

many others situations.5 

Although the use of threaded fasteners provides benefits and design options to a designer, there 

are environmental conditions that can have an adverse effect on the design. When a designer 

purchases and uses a threaded fastener, it is often for, “the clamping force provided by the action 

of the fastener and tapped hole, or the fastener and a nut.”6 However, preload in the fastener can 

be eliminated by the mechanism of vibration loosening,7

 which in some situations can actually 

result in the fastener being totally removed from the assembly.8 

Many researchers have conducted experiments with the goal of identifying parameters of 

threaded fastener design that contribute to the self-loosening of the joints. They have been 

trying to identify why fastener loosening can unintentionally occur as a result of operational 

conditions.9

 

 

4

 Anon 16 

5

 Anon 16 

6

 Anon 16 

7

 Bickford An Introduction 60 

8

 Anon 18 

9

 Bolt Science 
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Nevertheless, “in spite of numerous advances in fastener design, materials and techniques, the 

problem of fastener loosening is all too prevalent.”10 Additionally, even though the phenomenon 

of unintentional vibrational loosening is accepted by many as a real issue, it is widely 

misunderstood by many Engineers.11 As summarized by Ramey and Jenkins, 

“The threaded fastener, or bolt, is one of the most common connecting devices. 

Used in a wide range of applications, one would expect that the knowledge of 

how a bolt performs under certain loading conditions would be well known. 

While the behavior of bolts under static tensile and shear forces is fairly well 

understood, their behavior under dynamic loads, such as vibration, is not.”12

Threadlocking devices are one solution to the problem of threaded fastener loosening. There are 

many devices available and the American National Standards Institute (ANSI) Subcommittee 

B18:20 identified three basic locking fastener categories: free spinning, friction locking and 

chemical locking.13 This literature review will only cover the chemical locking category, which 

includes anaerobic adhesives that fill and bond gaps between the male and female threads.14

J.3 Chronology 

Since the issue of self-loosening of bolted joints has been around for decades, there are numerous 

reports and studies that have been conducted that reflect progress with respect to a better 

understanding of the topic. Adapted from a survey or review of work on dynamic loosening by 

Hess, the following chronology is a brief summary of published work on self-loosening of 

threaded fasteners. This review is intended only as an overview of the published knowledge on 

this topic. See original sources if more detailed information is needed. 

1945 Goodier and Sweeney started from the idea that “loosening would be a consequence of 

mere fluctuation, not necessarily rapid, of bolt tension, formed a theory of the mechanism of 

loosening, and carried out an experimental investigation of it in ordinary tensile test machines.”15

1950 Sauer, Lemmon, and Lynn conducted “experimental tests that examined the effect of 

alternating cycles of axial loading, dynamic to static load ratio, contact surface condition, and 

misalignment on loosening of threaded components.”16

 

10 Anon 16 

11 Bolt Science 

12 Ramey and Jenkins 1 

13 Bolt Science 

14 Bolt Science 

15 Goodier and Sweeney 789 

16 Hess in Bickford 
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1966 Clark and Cook “investigated the effect of fluctuating torque on loosening of a tightly 

sealed bolt. They pointed out that while it is true, in many machine situations, that fluctuating 

tension remains the primary component of load on the bolt, there are also many situations in 

which two mating parts held by a bolt rotate a minute amount with respect to one another.”17

“The results of the tests show that bolt loosening is a function of both oscillatory torque 

amplitude and initial shank stress.”18 Specifically, “as the amplitude of the oscillatory torque is 

reduced, a larger number of cycles are required for bolt loosening, until eventually the bolt will 

apparently endure a certain level of fluctuating torque indefinitely. This finding led them to the 

conclusion that “accidental overloads contribute more to bolt loosening than do continuous 

repetitive oscillatory torques of small amplitude.”19 

1966 The Elastic Stop Nut Corporation of America (ESNA) conducted testing that “resulted in 

the first theory on shock-induced loosening.” “The theory is based on the idea that shocks or 

impacts to a bolted assembly will cause the components to resonate and loosen.”20 “Test data 

from experiments show that the number of impacts and the severity of the impacts are the two 

variables that promote loosening failure. Frequency of the impact was not found to have an 

effect, except that a certain number of blows can be struck in less time if the frequency is 

raised.”21 “The fixture ESNA used for their experiments is described in MIL-STD-1312-7A.”22

1968 Gambrell presented “a series of experiments to examine how loosening is influenced by 

bolt thread series (coarse or fine), initial preload, lubrication, dynamic/static load ratio (DSR), 

frequency of loading, and number of cycles of load application.”23 The “axial cyclic tension was 

applied to the test joint by a variable-speed electric motor driving a cam and follower that 

activates a load lever.”24

1969 Junker discussed the self-loosening of preloaded bolted connections when subjected to 

vibration. Specifically, he presented a new machine design that yielded quantitative data for 

evaluating locking properties.25 He proposed a unique test method and apparatus to make it 

possible to reproduce conditions of vibration that are not only certain to loosen bolted joints, but 

which also closely simulate actual assembly conditions. He showed that preloaded fasteners can 

 

17 Hess in Bickford 762 

18 Hess in Bickford 764 

19 Hess in Bickford 764 

20 Hess in Bickford 765 

21 Hess in Bickford 766 

22 Hess in Bickford 766 

23 Hess in Bickford 767 

24 Hess in Bickford 767 

25 Junker 1969 314 
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loosen as a result of rotation, as soon as relative motion occurs between the mating threads and 

between the bearing surfaces of the fastener and the clamped material.26

1970 Koga “studied the loosening of threaded fasteners subjected to repeated impacts and he 

performed experiments, as well as developed a theory of loosening based on the theory of 

propagation of stress waves.”27 “Koga qualitatively showed that changing the angle of the thread 

and other details on the screw end could alter the amount of tensile waves propagated.”28

1973 Koga “used three-dimensional analytical geometry to quantitatively show the effect of 

thread angle on loosening of bolted joints.”29

1972 Finkelston of Standard Pressed Steel Co. (SPS), provided some suggestions for 

increasing vibration resistance to loosening, even though some identified are possibly 

uneconomical for designs that are optimized for weight and size. The suggestions were to 

“increase grip friction in the bolt by increasing preload or the number of bolts in the joint, 

eliminate relative motion in the joint by designing rigid members with little or no clearance, and 

to use fasteners that have high resistance to loosening.”30 His experiments were performed on a 

Junker type machine. 

1973 Walker “was the first to use fractional factorial experiments design concepts to 

investigate the influence of several variables or factors on the vibration life of fasteners.” “The 

factors evaluated were preload, prevailing torque, thread pitch, surface coating, and thread pitch 

diameter clearance.”31 Walker performed tests with two different machines: a Junker machine 

and the apparatus described in MIL-STD-1312-7A, in addition, the results from tests on both 

machines were reported to be in good agreement.32

1973 Junker stated that, “preloaded screws (or nuts) rotate loose, as soon as a relative motion in 

the thread takes place” and identified that this motion cancels the friction grip and originates an 

inner off-torque proportional to the thread pitch and to the preload. Additionally, the inner offtorque rotates the screw loose if the friction under nut or bolt head bearing surface is cancelled 

by relative motions.33

 

26 Junker 1969 314 

27 Hess in Bickford 773 

28 Hess in Bickford 774 

29 Hess in Bickford 774 

30 Hess in Bickford 774 

31 Hess in Bickford 776 

32 Hess in Bickford 776 

33 Junker Feb 1973 (final) 23 
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1973 Pearce gave a preview of locking fastener types, benefits, and problems. Specifically, he 

identified and categorized free spinning fasteners, friction locking fasteners, and chemical 

locking fasteners, of which he advocated for the chemical locking type to be the best option for 

preventing fasteners from loosening due to vibration.34

1974 Hardiman discussed the use of anaerobic adhesives for converting threaded fasteners to a 

locking fastener system. He claimed that anaerobic adhesives could develop sufficient locking 

torques for a wide range of surface conditions and in his paper he provided a general overview of 

what anaerobic adhesives are, how they work, and advantages for using them in design.35

1978 Sakai “performed a series of theoretical analysis and experiments on bolted 

assemblies.”36

1979 Sakai “investigated the loosening of bolts tightened over their yield point and subjected 

to tensile load.” He presented a theoretical analysis, along with static and dynamic experiments 

that were reported, and he concluded that “tightening bolts over their yield point has no 

disadvantage” with respect to loosening. Additionally,” it was found that the fatigue life of bolts 

tightened over their yield point was longer than that of bolts tightened in elastic range.” The 

reason for this finding was assumed to be attributed to having a larger clamping force resulting in 

a smaller load on the bolt, which corresponds to a longer fatigue life.37

1980 Kerley discusses issues encountered with bolted connections, including the effects of bolt 

tightening methods on structure stresses, verification of axial preload procedures, design 

considerations for shear loaded joints, locking features, and failure analysis.38

1981 Haviland identified ten myths, or fables, he found throughout literature, or in designers 

minds, and provided the facts about each. He presented these with the objective of assisting with 

the achievement of better understanding development of predictable clamp load, prevention of 

self-loosening, and maintenance of the ability to disassemble the joint by avoiding galling and 

corrosion.39

1982 Kerley believed that time-related failures were strictly an engineering problem that could 

be avoided with good design. Therefore, he presented an overview of the concept of bolt 

 

34 Pearce 1-4 

35 Hardiman 1 

36 Hess in Bickford 776 

37 Hess in Bickford 779-780 

38 Kerley Nuts and Bolts 1980 

39 Haviland 1 
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analysis with the intent for designers to use the existing analytical and testing methods to help 

prevent failures.40

1983 Haviland proposed that the limitations of fasteners are not always well understood and 

therefore looked at how a screw fastener generally works, and how to make it more reliable as 

well as cost effective in use. He reviewed clamping force, choosing a correct bolt, selection of a 

safe design load level, loosening tendencies, how to keep the joint tight, testing with transverse 

shock, and prevention of premature loosening.41 

1983 Bickford stated that, “the behavior of a joint in use depends on the preload in the bolts in 

use, not the preload introduced by the mechanic.” He continued that getting the correct initial 

preload in a bolted joint is very difficult to do and that if torque is being used to tighten the 

fasteners, for example, there are some 76 variables that affect the relationship between achieving 

the desired preload.42 Additionally, he identified another mechanism that can eliminate all initial 

preload in a fastener and is known as vibration loosening, under which the fastener first loses 

preload gradually for some time. However, once the residual preload in the fastener has fallen so 

far that it is no longer able to prevent transverse slip between male and female threads, or nut and 

joint surfaces, then the loosening action becomes far more rapid and can result in total loss of the 

nut.43

1983 The American Society of Mechanical Engineers (ASME) and American National 

Standards Institute (ANSI) B-18 Subcommittee on the Loosening Mechanisms of Bolted Joints 

Under Vibration was formed in the early 1980’s. The subcommittee was active at least until 

1987, until extended funding for the comprehensive research plan was not acquired and the 

members of the subcommittee disbanded.44 Peter P. Zemanick was the chairman of the 

committee and James Kerley, of NASA GSFC, was also a member during the duration of the 

team. The subcommittee had a proposal for a comprehensive experiment plan to study (test and 

evaluation procedure) that would be used to study vibration loads in bolted joints, of which they 

were “trying to provide the first real understanding of the reasons fasteners loosened.”45 

Research by the subcommittee would have included analysis of finite-element and probabilistic 

models, as well as exploratory and milestone tests and the variables they wanted to test were to 

include: thread pitch, clearances, fit, length to diameter ratio, direction of vibration, frequency of 

vibration, and joint damping properties.46 One of the specific goals and proposals of the research 

 

40 Kerley the use and miss use 1 

41 Haviland 1983 16 

42 Bickford That Initial Preload 57 

43 Bickford That Initial Preload 60 

44 Hess in Bickford 782 

45 Bickford Fastener Groups Seek Answers to Bolted-Joint Problems 80 46 Bickford Fastener Groups Seek 80 
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plan was to identify mathematical relationships that govern loosening based on the study of 

simple joints, such as beams, and then apply them to the design of more complex structures.47 

1983 Light summarized a comprehensive nine-year study on vibration loosening of threaded 

fastenings performed by the British Aircraft Company and funded by the British Ministry of 

Defense. The study examines existing test equipment, develops models and analyses, and 

provides comparative test data using a Junker type test machine. Loctite® adhesives, Durlock 

bolts and Huckcrimp fasteners were found to perform the best of the dozens of locking features 

tested. 

1984 Yamamoto and Kasei “proposed a new mechanism of self-loosening of bolt and nut 

joints subject to transverse vibration,” which “attributes self-loosening rotation of a nut to the 

accumulation and release of potential energy due to torsional bolt deformation.”48 They 

developed quantitative models based on a two-stage theory for the nut to slide along the thread of 

the bolt, however, there were no quantitative results provided for model verification.49

1984 Kerley conducted testing on Spiralock® nuts under vibration and static load conditions 

and found that, “the most severe vibration tests did not loosen the nuts when subjected to both 

high amplitude sine and random testing.”50

1985 Charles reported that in order to improve the performance of threaded fasteners in 

conditions under vibration, adhesives could be used as a preventive option, and may also be 

considered perhaps the most simplest and easiest of all locking systems.51

1986 Haviland identified variables that affect the cure speed and initial strength of adhesives 

that are used as locking mechanisms.52

1987 Kerley used an application of the method of retroduction to analyze the topic of selfloosening of bolted joints for why and how nuts back off during vibration.53 

1989 Vinogradov and Huang numerically investigated only one aspect of the problem of selfloosening of bolted joints, explicitly, the effect of frequency of vibrations.54 They noted in their 

 

47 Pai and Hess 2003 Inf of Fastener 618 

48 Hess in Bickford 786 

49 Jiang, Zhang, and Lee A study 2003 518 

50 Kerley 3 

51 Charles 165 

52 Haviland 55 

53 Kerley NASA TM4001 

54 Vinogradov and Huang 136 
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conclusions that the inertial mechanism of self-loosening is triggered by the non-even 

distribution of the preload forces along the thread, and followed that joints with more even 

distribution of preload forces should be less susceptible to vibration loosening.55 

1990 Bickford provides an overview of how vibration loosens a nut, Junkers theory of 

vibration, testing option for simulated joint connections, and suggestions for how to resist 

vibration.56

1992 Daadbin and Chow studied the loosening due to impact load using a mass-spring model 

and “it was argued that in the occurrence of resonance, the nut thread would separate from the 

thread of the bolt and the nut would undergo a free flight until it touched the inclined surface 

again.” 57 A series of experiments were conducted to verify the theory, however, the preload 

applied in the experiments was not realistic for the bolt sizes used in their experiments.58

1995 The objective of the study by Ramey and Jenkins was to identify the main design 

parameters contributing to the loosening of bolts due to vibration and to identify their relative 

importance and degree of contribution to bolt loosening. The report stated that, 

“Vibration testing was conducted on a shake table with a controlled-random input in 

the dynamic testing laboratory of the Structural Test Division of MSFC. Test 

specimens which contained one test bolt were vibrated for a fixed amount of time and 

a percentage of pre-load loss was measured. Each specimen tested implemented some 

combination of eleven design parameters as dictated by the design of experiment 

methodology employed. The eleven design parameters were: bolt size (diameter), 

lubrication on bolt, hole tolerance, initial pre-load, nut locking device, grip length, 

thread pitch, lubrication between mating materials, class of fit, joint configuration, 

and mass of configuration. These parameters were chosen for this experiment because 

they are believed to be the design parameters having the greatest impact on bolt 

loosening.”59

The investigation results indicated that nut locking devices, joint configuration, fastener size, and 

mass of configuration were significant parameters in bolt loosening due to vibration.60

1996 Hess and Davis reported on a series of experiments they conducted to examine the 

motions of threaded fasteners subjected to axial harmonic vibration. Particularly, a significant 

 

55 Vinogradov and Huang 137 

56 Bickford An Introduction 440-466 

57 Jiang, Zhang, and Lee 2003 A study 518 

58 Jiang, Zhang, and Lee 2003 A study 518 

59 Ramey and Jenkins i 

60 Ramey and Jenkins i 
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relative twisting motion is found to occur against and with the load, therefore indicating that the 

components can loosen or tighten due to vibration. The direction of twist was shown to depend 

on the frequency and amplitude of the vibratory input in addition to other physical parameters. 61 

1996 Hess, Basava, and Rasquinha examined fasteners subject to axial vibration and found that 

they can experience either loosening or tightening.62 Specifically, they studied the effect of 

vibration level and initial preload on the clamping force and concluded that, with high preloads 

and/or low vibration levels, the clamping force remains steady over a large number of cycles, 

however, as the preload decreases and/or the vibration level increases, first loosening then 

tightening of the assembly occurs.63

1996 Johnson reported tests results that indicated a failure to maintain dimensional size 

conformance for standard fasteners can lead to degraded vibration resistance.64

1997 Hess and Sudhirkashyap presented a dynamic model of a single-bolt assembly with 

moderate preload subjected to axial harmonic vibration and found that depending on the applied 

vibration amplitude and frequency, along with other system parameters such as preload, contact 

stiffness, mass of the clamped components, coefficient of friction and thread fit, can be tuned to 

make either loosening or tightening of the joint occur. 65

1998 Dong and Hess reported on the development of a test apparatus and procedure to evaluate 

threadlocking adhesive life when in an environment of accelerated vibration. They found an 

inverse power relationship that is present between the threadlocking adhesive life and the applied 

vibration level.66 

1998 Hess provided a chapter on vibration and shock –induced loosening in a bolting 

handbook. This work includes a survey of theoretical analysis and experimental work spanning 

over five decades, general design guidelines for minimizing fastener loosening, an overview of 

fastener locking techniques, and descriptions of test fixtures and test machines that have been 

used to assess fastener loosening under dynamic conditions.67

1999 Dong and Hess presented the results from dynamic tests that investigate the effects of 

threaded dimensional conformance of fasteners on vibration induced loosening. The data show a 

 

61 Hess and Davis 417 

62 Hess, Basava, and Rasquinha 97 

63 Hess, Basava, and Rasquinha 101 

64 Hess in Bickford 806 

65 Hess and Sudhirkashyap 311 

66 Dong and Hess 816 

67 Hess in Bickford 757 
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significantly degraded resistance to vibration for fastener combinations with undersized pitch 

and major bolt diameters, or oversized pitch and minor nut diameters, compared to fasteners 

within conformance. 68

2002 Pai and Hess used a three-dimensional finite element model to study details of four 

different loosening processes that are characterized by combinations of complete or localized slip 

at the head as well as thread contacts. Results of the finite element analysis show that it is 

possible to have loosening at relatively low shear loads (i.e., lower than previously expected) due 

to localized slip.69

2003 Jiang, Zhang, and Lee studied both an experimental investigation and a finite element 

analysis to explore the mechanism of the early stage self-loosening of bolted joints under 

transverse cyclic loading.70 The experimental and finite element simulations suggested that 

friction between the clamped plates had an insignificant influence on the early stage of bolt selfloosening when transverse displacement is a controlling factor. 71 It has been widely known for 

many years that relaxation and embedment occurs in the early stages of loosening under dynamic 

loading. 

2003 Pai and Hess identified that, 

“Recently, new experimental and three-dimensional finite element analysis results 

have helped identify the minimum shear forces required to cause loosening and also 

understand details of the underlying mechanism of loosening. It was shown that in 

some cases, loosening in joints occurs due to localized slip when the fastener is 

subjected to a dynamic shear force about half the magnitude required to cause 

complete slip at the fastener bearing surface.”72 

The objective for this paper was to develop a procedure to identify regions in an assembly 

where the fastener would be least likely to fail due to loosening.73 They showed that it was 

possible to minimize the likelihood of fastener loosening failure by optimum placement of 

threaded fasteners. Since shear force is the main predictor of loosening, it was necessary to 

consider the effect of slip and side-contact in assemblies with significant slip, for example, 

when the slip is greater than hole tolerance. 

 

68 Dong and Hess 209 

69 Pai and Hess 383 

70 Jiang, Zhang, and Lee 2003 A Study 518 

71 Jiang, Zhang, and Lee 2003 A Study 525 

72 Pai and Hess 2003 Infl of Fastener 617 

73 Pai and Hess 2003 Infl of Fastener 617 
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2004 Gillis reported on the use of Spiralock® for the NASA Cassini-Huygens mission. The 

product was selected since it is able to survive the vibration and high temperature launch 

environment, while also keeping a tight seal for the necessary design components.74

2004 Pai and Hess presented a fundamental analysis and experiments which revealed that a 

fastener can loosen at lower loads than previously expected due to localized slip at the contact 

surfaces and experimental results confirmed this phenomenon.75

2004 Results derived by Jiang, Zhang, Park, and Lee are that the relative displacement of the 

two clamped plates is the major factor in self-loosening, a larger initial clamping force will result 

in a higher self-loosening resistance, although may lead to bolt fatigue failure, and that when all 

other conditions are the same, the use of a washer with a regular nut is better than use of a flange 

nut.76

2004 Zhang, Jiang, and Lee conducted an experimental investigation to study the effects of 

clamped length and loading direction on the self-loosening of bolted joints.77 For a constant 

preload for each experiment, the joint was subject to cyclic external loading, while the relative 

displacement between the two clamped plates was a controlling factor.78 The conclusions for 

their study were that: increasing the clamped length can enhance the self-loosening endurance 

limits in terms of the controlled relative displacement of the two clamped plates, even though the 

load carrying capability was not influenced significantly due to the plate thicknesses. 

Additionally, they stated that it was clear having an external load applied in any direction 

different from the pure shear loading direction would increase the load carrying capability and 

enhance the self-loosening resistance.79

2005 Chen, Hsieh, and Lee investigated the effects of thread lead angle, initial preload, 

vibration frequency, and the nature of material on bolt loosening behavior. The approach they 

identified analyzes static and dynamic behaviors, as well as if the bolt is within the elastic range, 

and is intended as a guide for design a procedure to avoid failures due to vibration.80 The main 

purpose of this paper was to offer an approach to investigating the effects of various factors, 

static and dynamic, that loosen bolts.81

 

74 Gillis 1 

75 Pai and Hess 2004 19 

76 Jiang, Zhang, Park, and Lee 930 

77 Zhang, Jiang, Lee 129 

78 Zhang, Jiang, Lee 129 

79 Zhang, Jiang, Lee 135 

80 Chen, Hsieh, Lee 299 

81 Chen, Hsieh, Lee 313 
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2005 Ibrahim and Pettit provided an overview of problems associated with the structural 

dynamics of bolted joints and identified that the problems are complex since every joint will 

involve different uncertainties, as well as non-smooth and non-linear characteristics.82 

Therefore, they provided recommendations for future research areas including experiments that 

address: additional sinusoidal and random excitation tests that incorporate variability in 

mechanical properties, various values of preload, long test durations, influence of preload 

uncertainty on both natural frequency and damping ratio, prying loading, friction forces, and 

relaxation effects.83 

2005 Nassar and Housari used both a mathematical model and an experimental procedure to 

study the effect of thread and under head coefficients, the hole clearance, and the frequency and 

the amplitude of the transverse excitation.84 The results were that thread lubrication has a more 

significant effect than under head lubrication, the clamp load loss may or may not be affected by 

the bolt hole clearance, although it is significant when the external excitation is large enough to 

cause the bolt head to slide and contact with the edge of the hole, and that frequency does have 

an effect on fastener self-loosening, since lower frequencies cause more loosening. 

J.4 Parameters 

The results of these reports have identified many parameters as positively contributing, and 

others as hindering, the success of a bolted joint subject to vibration. As a summary of the work 

done by the previously mentioned researchers, the following information provides a listing of the 

parameters considered to significantly affect the fastener when vibration is a part of the 

environment for a given product. Bear in mind, there are studies conducted by the Air Force, as 

well as others, which have identified at least 76 variables that affect the friction constraints 

between nuts and bolts.85 Therefore, the following parameters were selected to be studied based 

on the context of current research and many have been identified and specifically tested in 

experiments, while some have been tested only analytically, and still other factors have not yet 

been analyzed. 

First, it is important to be aware that there are multiple causes of failure of a fastener. 

For example, “self-loosening is commonly caused by vibration but can also be caused by 

temperature or pressure cycles.”86 Fatigue and self-loosening are the most frequent causes of 

failure of dynamically loaded bolted joints.87 Furthermore, there are two major types of 

 

82 Ibrahim and Pettit 857 

83 Ibrahim and Pettit 913-914 

84 Nassar and Housari 169 

85 Bickford Faster Groups Seek 80 

86 Dong and Hess 1998 816 

87 Anon 16 
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vibration which have been found to affect a bolted joint, these are axial and transverse. 88 It has 

been determined, by experimental studies, that non-locking fasteners rotate completely loose 

under transverse vibration. 89 Generally, it is agreed that vibration is a far greater problem in a 

joint loaded in shear than only in tension, since the axial loading may only succeed in reducing 

preload only by about 30 to 40 percent over a long period of time.90 Usually, the axial vibration 

alone will not result in total loss of preload or in complete loss of the fastener.91 Transverse 

vibration is definitely more hazardous to bolt vibration loosening than an axial dynamic load. As 

a result, designers can minimize the slip by orienting the bolts and joints to have axes parallel to 

the expected direction of vibration.92

Initially, consider the situations that are necessary for vibration loosening of a bolted joint. 

Bickford discussed the concept of “essential conditions” for situations that effect fasteners in an 

assembly.93 He stated that self-loosening of the fastener has only two requirements: cyclic loads 

at right angles to the bolt axis and relative motion (slip) between nut, bolt, and joint members.94 

Continuing with the discussion, Bickford states: 

“The fact that the essential conditions are limited make it appear that it would be 

relatively easy to avoid joint failure. The problem, however, is that dozens – maybe 

even hundreds – of secondary conditions can establish the essential conditions 

required for a particular type of failure.”95

These secondary conditions include some of the parameters that researchers have studied to 

better understand vibration loosening. 

There are many factors, or secondary conditions, that influence bolt loosening, possibly 80 to 

100 of them. Ramey and Jenkins chose to study 11, of the 80 to 100, they believed were 

dominant including: bolt size (diameter), lubrication on bolt, hole tolerance, initial preload, 

locking device, grip length, thread pitch, lubrication between mating surfaces, class of fit, joint 

configuration, and mass of configuration. 96 However, in addition to these design parameters, 

they also considered input factors as well, including: vibration direction, vibration level, 

vibration frequency, and duration of vibration. 97 Anon identified that self-loosening can occur 

when clamping “soft” materials, such as a gasketed cover, where bolt tightness is then often 

 

88 Anon 16 

89 Hardiman 

90 Bickford An Intro 443 

91 Bickford An Intro 443 

92 Bickford An Intro 454 

93 Bickford An Intro 431 

94 Bickford An Intro 431 

95 Bickford An Intro 431 

96 Hess in Bickford 793 

97 Hess in Bickford 793 
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determined by the capability of the gasket to support the load.”98 Although, even “hard” flanges 

and gaskets have been identified as having the potential to collapse under the clamping load if 

there are burrs under the head or poor finishes on the threads, which is a condition called brinneling.99 

Many of the reports state that preload and friction are the most important factors in a joint to 

prevent loosening especially in the absence of any secondary locking. Hess states that this is due 

to the fact that thread and head friction are physically what provide resistance to loosening in a 

standard threaded fastener, and this friction is proportional to preload. Therefore, the higher the 

preload, the higher the head and thread friction (for given surface conditions and lubricant) and 

the higher the resistance to loosening. Bickford notes that for the average bolt-nut combination, 

the best assurance against shock damage and vibration failure is a tight bolt.100 Kerley has also 

documented the importance of preload under dynamic load conditions.101 The list of researchers 

that support the importance of preload go on to include, but are not limited to: Basava, Chen, 

Haviland, Hess, Hsieh, Ibrahim, Jenkins, Junker, Lee, Light, Pai, Pettit, Ramey, and Zhang. 

Preload values are definitely an important consideration for design. In one situation, threads 

were completely locked together by adhesive, but bolt preload was not sufficient to prevent joint 

movement and caused the bolt to be partially worn away.102 Bickford has explicitly stated that, 

“severe transverse vibration, perpendicular to the axis of the bolt, can, and often does, cause 

complete loss of preload.103 Again, reiterating the importance of preload and importance for the 

designer to consider it an essential parameter with respect to self-loosening of fasteners. 

Another factor that has been considered important by researchers is the length-to-diameter ratio 

of the bolt. It has actually been claimed that if a bolt has a length-to-diameter ratio of 8:1 or 

greater, it will never vibrate loose.104 With the use of long, thin fasteners instead of slipping 

when under transverse vibration, the fasteners will bend.105 Along similar lines, Sakai revealed 

that the larger the thickness of the clamped parts, the smaller the clearance between the male 

screw and the female screw, the larger the clamping force, and the smaller the diameter of the 

bolt, then the less liable the bolt is to loosen.106 Pai and Hess have also suggested design 

guidelines to avoid loosening including tighter tolerances, bolts with large length-to-diameter 

ratios, as well as a larger preload to avoid slip, not just gross slip, but also localized slip.107 

 

98 Anon 18 

99 Bickford An Introduction 61 

100 Kerley 1980 16 (20 of doc) 101 Kerley 1980 3-41 (99 of doc) 102 Bolt Science 103 Bickford An Intro 443 104 Bickford That Initial Preload 61 105 Bickford An Intro 455 106 Sakai 1387 107 Pai and Hess 2003 Infl of Fastener 619 
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In some situations, the experimental results of multiple researchers do not agree. For example, 

Junker initially found no influence of frequency on the self-loosening of fasteners when he tested 

a non-locking screw.108 Later he stated 

“Tests show that the self-loosening of screws is independent of frequency. It simply 

depends upon the occurrence of relative motions and on the length of such motions 

during one cycle. If the forces causing these relative motions are inertia forces, they 

are a function of the square of the frequency. In this case the frequency indirectly 

influences the loosening process”109

Conversely, Kerley discussed some of his own experimentation, as well as how he shared the 

same view as Haviland, when he stated, 

“Tests were performed at GSFC to verify the Haviland theory. When the structure 

was vibrated at the low frequency, high-amplitude loads (5 g), the nuts backed off in 

a matter of seconds. When 20 g was applied at 1000 Hz, the bolts had not moved after 

10 minutes. In similar fashion, to simulate the multifrequencies of vibration that can 

occur, random vibration was applied. At 10 grms from 20 to 400 Hz, the nut 

separated in seconds. At 10 grms from 200 to 2000 Hz, the bolts did not move in 10 

minutes. These tests substantiate the theory that low-frequency excitations cause a 

bolt to back off.”110 

Kerley even continued to say that it was possible to keep deflections low in vibration by 

clamping an assembly on both ends and causing a higher resonant frequency with lower 

deflections. 111 Again, he referenced Haviland’s theory that large shearing deflections at a low 

frequency cause bolts to loosen.112 Further, it was reported that by changing the external load 

frequency slightly away from the resonant frequency, high levels of vibration, slip and fastener 

loosening ceased. Hess states that the reason why Kerley’s low frequency test resulted in 

loosening is that a much larger displacement motion and slip occurred with the lower frequency 

vibration test. In Kerley’s work, the vibration amplitude in units of displacement are 0.65” at the 

bolt for the low frequency dwell test and 0.0025” for the high frequency test. 

Vibration induced loosening of threaded fasteners is not completely understood as suggested 

here: 

“Our knowledge of vibration loosening is entirely empirical, and there are many 

factors which can make a difference. Some experiments, in fact, have suggested that 

complex interactions between suspected factors, perhaps more than the factors 

 

108 Junker 1969 109 Junker 1973 110 Kerley 1980 131 (197 of doc) 111 Kerley 1980 133 (201 of doc) 112 Kerley 1980 133 (201 of doc) 
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themselves, determine the rate at which a given system will loosen; and/or that there 

probably are other factors which we have not been able to pin down as yet, which 

also make a difference. You could easily be fooled by some of these unknown 

interactions and factors if you tested only a “test joint””113

For example, Walker reported that thread pitch and prevailing torque, along with a strong 

interaction between the two were found to be the most significant factors out of those he was 

considering in his experiment.114 As already mentioned, there may be more of these interactions, 

which have not been addressed thus far, and they may not be as apparent until they are explicitly 

considered. 

Now consider the addition of an anaerobic adhesive locking element to the bolted joint. Even 

though there are many parameters that can contribute to the effectiveness of the joint in a 

vibration environment, considering the use of adhesives adds to the complexity of the situation. 

The effectiveness of an adhesive can be contributed to many different parameters. Haviland 

noted that, 

“Machinery adhesives, like any durable plastic, can be made to fail by any one or a 

combination of mechanisms. Examples of such mechanisms are: molecular 

breakdown by strong chemical reaction, salvation, absorption, stress cracking, 

mechanical stressing, delamination of adhesion, and desorption, all of which are made 

more rapid by elevated temperatures. It is rarely necessary to test these phenomena 

individually because machinery adhesives usually are confined within metal parts that 

protect the adhesive from exposure except for a very thin bondline. The exposure of 

only a thin bondline suggests the most important requirement for long-term chemical 

resistance.”115

The variables of cure speed and initial strength can also be affected by factors such as, presence 

of air, gap or volume cured, active or inactive surfaces, primer and activator types, temperature, 

humidity, and finish of the parts.116 In a study of accelerated vibration life testing completed by 

Dong and Hess, preliminary tests revealed that failure was caused by a combination of preload 

loss and adhesive degradation. 117 Their conclusions suggest their test approach could be 

developed into a standard life test for threadlocking adhesives.118 

 

113 Bickford An Intro 450 

114 Hess in Bickford 776 115 Haviland 1986 78 116 Haviland 1986 55-67 117 Dong and Hess 817 118 Dong and Hess 817
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With this current state of experimental knowledge about the vibration loosening of threaded 

fasteners, it is still possible to provide general recommendations for designers and users. 

Adapted from Bickford and Sauer, here is a list of general guidelines and suggestions for bolted 

joint design: 

• Keep the friction forces in thread and joint surfaces from falling below the 

forces which are trying to loosen the nut 

• Mechanically prevent slip between the nut and bolt or nut and joint surfaces 

• Reduce the helix angle of threads to reduce the back-off torque component 

• Provide “prevailing torque” or locking action of some sort which counters the 

back-off torque created by the inclined planes of the threads, and does so even 

after friction forces in the system have been overwhelmed by vibration.119

• Properly specify the working loads so that the dynamic load will not approach 

or exceed the static tensile load originally developed in the tightening 

operation, results indicate that it is desirable to keep the dynamic/static load 

ratio in the range of 0.7 or less 

• Adequately control the method of manufacture, fabrication, assembly, and 

maintenance so as to have all contact surfaces at the threads, base of nut, and 

head of bolt in the best possible condition of cleanliness and smoothness 

• Improve alignment, as it results in better mating of the contacting parts in 

somewhat the same manner as does removal of dirt, grease, or surface 

irregularities120

J.5 Testing 

Since vibration loosening is not understood well enough to use mathematical models to predict 

loosening in an assembly, tests must be conducted with test machines.121 There are different 

options for test fixture designs that researchers have used. One of the most useful test designs is 

the Junker transverse vibration machine. Basically, this machine measures residual preload, 

applied dynamic transverse force, transverse displacement, and number of applied transverse 

cycles for a fastener under test. A Junker machine is shown in Figure J.1. Additionally, this 

machine is the basis for a German standard, Deutsches Institut für Normung (DIN) 65151.122 

Jiang et al. state that their particular version of the machine lacked displacement control.123 

However, most Junker type machines provide very accurate displacement control and 

measurement using an adjustable eccentric and an LVDT. Many researchers (e.g., Light, Hess, 

 

119 Bickford An Intro 453 120 Bickford An Intro 121 Bickford An Intro 450 122 DIN 65151 123 Jiang, Zhang, Park, and Lee 
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etc) and organizations, such as Loctite,124 Nord-Lock,125 and Hard Lock Industry Co., Ltd.126 etc 

use a Junker type machine for testing and assessing locking features of threaded fasteners. 

Figure J.1. Junker Vibration Test Machine 

Another experimental test fixture used is the Aerospace Locknut Manufacturer’s Association 

(ALMA) test, also designated as the MIL-STD-1312-7 or more recently the NASM-1312-7 

vibration test. It has been stated that the ALMA test fixture design is easy to setup and run127, 

however, 

“Some people, however, believe that it is more pertinent to measure the actual 

magnitude of the force exerted on the joint under test and/or the actual displacement 

of joint members. This is not possible with the ALMA test. You can measure the 

amplitude of the shake table, but it is difficult to tell what, if any, displacement has 

actually resulted between the fastener and the test cylinder – or determine the forces 

 

124 Loctite 

125 Nordlock 

126 Hardlock 

127 Bickford An Intro 451 
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on the fastener – because both of these depend on impact, and impact is very difficult 

to predict or control.”128

Figure J.2 shows a picture of an ALMA test fixture designed to test one bolt. 

Figure J.2. ALMA Test Fixture Example129

Haviland and Kerley used another type of vibration test fixture. It consisted of a compound 

beam mounted to a vibration shaker machine. In this design, the bolted joint being tested clamps 

the beam, which induces shear to the fastener as a result of bending of the beam.130 Figure J.3 

shows one example of this apparatus. Dong and Hess also used this type of fixture when they 

conducted accelerated vibration life tests of threadlocking adhesives.131

 

128 Bickford An Intro 451 

129 Bickford (book ) 1990 130 Kerley NASA TM 4001 15 (21 of doc) 

131 Dong and Hess Acceled Vib. 816 
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Figure J.3. Kerley Test Fixture Design132

Other test fixtures have focused on the axial loading of the fasteners, but since the focus of many 

of the reports have been on transverse loading, a discussion on axial fixture designs is not 

provided here. 

Each of the researchers have taken the approach that, the most common and easiest way to 

loosen a bolted assembly is by inducing transverse slip.133 However, it has been identified by 

Haviland, of Loctite® Corporation, that, 

“Predicting the suitability or life of any material for a particular application or 

environment is difficult without extensive field tests that duplicate the proposed 

environment. This is especially true for adhesive systems because the adhesive is 

only half of the system.”134

Possible dynamic tests should be performed on the system itself.135 Of course, theoretically, 

when you test a fastener for vibration resistance, you would like to subject it to the vibration 

 

132 From Kerley NASA TM 4001 pg 46 of report 

133 Haviland 1983 

134 Haviland 1986 78 

135 Bickford An Intro 450 
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frequencies and magnitudes you expect the joint to encounter in your application, but predicting 

the vibration environment in a given product is even more difficult than predicting external 

loads.136 This is not widely agreed upon. Bickford notes that the “only recourse is to provide a 

fastener system that is immune to the range of frequencies you expect it might encounter in 

practice and then to determine by trial and error whether or not you have been successful.”137

It should also be noted that the ASME/ANSI subcommittee previously mentioned started to 

screen fastener testing equipment that would be best appropriate for conducting experiments.138 

However, no reports on their findings have been located through an extensive search in multiple 

library databases, as well as contacting members of the organizations directly.139, 140

J.6 Summary 

With regards to the self-loosening of bolted joints, there are many experiments and research 

studies that have been completed to develop theories and models, and to assess and compare 

locking features performance. Some of the theories are more widely accepted than others, 

although many agree that the topic is broad and a full understanding of the issue has not been 

accomplished thus far. It is generally agreed upon by researchers that, “dynamic transverse 

forces are more dangerous than dynamic axial forces”141 from a loosening perspective. This has 

led to a couple test fixture and test machine designs that have been used to study the loosening of 

threaded fasteners. 

There have been many researchers that have helped improve our understanding of how fasteners 

react to different environments, specifically vibration. However, none have derived end-all 

solutions for the loosening problem. It has been identified that the comprehensive research plan 

the Subcommittee on the Loosening Mechanism of Bolted Joints Under Vibration created was 

not performed due to a lack of funding for the research.142 Consequently, the group did not 

continue with the test plan, nor did organizations which hosted this subcommittee retain records 

of the fact that there was a subcommittee devoted to this topic, nor do the organizations have any 

documentation on any of the findings of the group, since all records, including meeting minutes, 

are discarded, based on company policy.143, 144

 

136 Bickford An Intro 452 137 Bickford An Intro 452 138 Pearce, M. B. 1 139 Personal Correspondence ASME 140 Personal Correspondence ANSI 141 Junker 1969 142 Hess in Bickford 782 143 Personal Correspondence ASME 

144 Personal Correspondence ANSI 
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The subcommittee stated that an extensive experimental analysis is necessary if a better 

understanding of the issue of self-loosening of bolted joints is necessary. This was done to a 

large extent in a nine-year effort by the British Aircraft Corporation and funded by the British 

Ministry of Defense. This work is summarized in the paper by Light with about 2,500 pages of 

test and analyses details in several reports referenced by Light. 
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 4. TITLE AND SUBTITLE

Performance Characterization of Loctite® 242 and 271 Liquid Locking 

Compounds (LLCs) as a Secondary Locking Feature for International 

Space Station (ISS) Fasteners

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Dube, Michael J.; Gamwell, Wayne R.

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14. ABSTRACT

Several International Space Station (ISS) hardware components use Loctite® (and other polymer based liquid locking 

compounds (LLCs)) as a means of meeting the secondary (redundant) locking feature requirement for fasteners. The primary 

locking method is the fastener preload, with the application of the Loctite® compound which when cured is intended to resist 

preload reduction. The reliability of these compounds has been questioned due to a number of failures during ground testing. 

The ISS Program Manager requested the NASA Engineering and Safety Center (NESC) to characterize and quantify 

sensitivities of Loctite® being used as a secondary locking feature. The findings and recommendations provided in this 

investigation apply to the anaerobic LLCs Loctite® 242 and 271. No other anaerobic LLCs were evaluated for this 

investigation. This document contains the findings and recommendations of the NESC investigation.

15. SUBJECT TERMS

International Space Station; Loctite®; liquid locking compounds; NASA Engineering and Safety Center

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