SD-SITT_Specification_Approved_12-1-15.pdf

Specification

For

Shock Isolator Test Tower (SITT)

1 Dec 2015

POC: Lt Bradley Peterson, Program Engineer

AFNWC/NIAA

DSN: 777-8745

DISTRIBUTION STATEMENT D: Distribution authorized to DoD and U.S. DoD contractors only for Administrative or Operational Use determined as of 15 October 2015. Other requests for this document shall be referred to ICBM Systems Directorate, Hill AFB, UT 84056-5816.

WARNING: This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C., Sec 2751 et seq.) or Export Administration Act of 1979, as amended, (Title 50 U.S.C., App 2401 et seq).

Violation of these export- laws is subject to severe criminal penalties. Dissemination of this document is controlled under DOD Directive 5230.25.

DESTRUCTION NOTICE: For classified documents, follow the procedures in DoD 5220.22-M, National Industrial Security Operating Manual, Chapter 5, Section 7, or DoD 5200.1-R, Information Security Program Regulation, Chapter 6, Section 7. For unclassified, limited documents, destroy by any method that will prevent disclosure of contents or reconstruction of the document.

SITT Specification 1 December 2015

Table of Contents

1. SCOPE

1.1 Document overview

1.2 Document Structure and Format

2 APPLICABLE DOCUMENTS

2.1 Government Documents

2.2 Non-Government Document

2.2.1 Specifications

2.2.2 Drawings

3 REQUIREMENTS

3.1 Definition

3.1.1 System Diagrams

3.1.2 Interface Definition

3.1.2.1 MSS Shock Isolator

3.1.2.1.1 Hydraulic and Mechanical Interface

3.1.2.2 LER Shock Isolator

3.1.2.2.1 Hydraulic and Mechanical Interface

3.1.2.3 LCC Shock Isolator

3.1.2.3.1 Pneumatic and Mechanical Interface

3.1.2.5 SITT External Interface Requirements

3.1.3 Government Furnished Property List

3.1.4 Government Loaned Property List

3.2 Characteristics

3.2.1 Performance Characteristics

3.2.1.1 Testing – General Characteristics

3.2.1.1.1 SI Test Position

3.2.1.1.2 Stroke

3.2.1.1.3 Extend/Retract Rate

3.2.1.1.4 Hold Position

3.2.1.1.5 Max Forces, Scenario 1

3.2.1.1.6 Max Forces, Scenario 2

3.2.1.1.7 Linear Displacement Data Recording

3.2.1.1.8 In-line Force Data Recording

3.2.1.1.9 Pneumatic Pressure Data Recording

3.2.1.1.10 Pneumatic Pressure

3.2.1.2 Testing – Applied Forces

3.2.1.2.1 LCC Shock Isolator

3.2.1.2.2 MSS Shock Isolator

3.2.1.2.3 LER Shock Isolator

3.2.2 Physical Characteristics

3.2.2.1 ESD

3.2.2.2 Size

3.2.2.3 Weight

3.2.3 Reliability

3.2.3.1 Availability/Reliability

3.2.3.2 Operating Life

3.2.4 Maintainability

3.2.4.1 Preventative Maintenance

3.2.4.2 Calibration

3.2.4.3 Accessibility for maintenance

3.2.4.4 Mean Time To Repair

3.2.4.5 Maintenance and calibration aids

3.2.4.6 Accessibility for repair and adjustment

3.2.4.7 Accessibility for adjustment/calibration

3.2.5 Environmental Conditions

3.2.5.1 Operating

3.2.5.1.1 Temperature

3.2.5.1.2 Humidity

3.2.5.1.3 Altitude

3.2.5.1.4 Fungus

3.2.5.1.5 Wind

3.2.5.1.6 Rain

3.2.5.1.7 Snow

3.2.5.1.8 Hail

3.2.5.1.9 Ice

3.2.5.1.10 Salt

3.2.5.1.11 Dust

3.2.5.1.12 Sunshine

3.2.5.1.13 Vibration

3.2.5.1.14 Shock

3.2.5.2 Non-Operating

3.2.5.2.1 Temperature

3.2.5.2.2 Humidity

3.2.5.2.3 Altitude

3.2.5.2.4 Fungus

3.2.5.2.5 Wind

3.2.5.2.6 Rain

3.2.5.2.7 Snow

3.2.5.2.8 Hail

3.2.5.2.9 Ice

3.2.5.2.10 Salt

3.2.5.2.11 Dust

3.2.5.2.12 Sunshine

3.2.5.2.13 Vibration

3.2.5.2.14 Shock

3.2.6 Transportability

3.2.7 Implementation

3.2.7.1 Firmware

3.2.7.2 Test Set Operation

3.2.7.3 Calibration

3.2.7.4 Visual Displays

3.3 Design and Construction

3.3.1 Materials

3.1.1.1 Materials, Processes, and Parts

3.3.1.2 Toxic Products and Formulation

3.3.1.3 Corrosion Prevention and Control

3.3.1.4 Dissimilar Metals

3.3.1.5 Electromagnetic Interference Characteristics

3.3.1.6 Finish

3.3.2 Nameplates and Product Markings

3.3.2.1 Labels

3.3.3 Workmanship

3.3.3.1 Cleaning

3.3.3.2 Threaded Parts

3.3.3.3 Bearing Assemblies

3.3.3.4 Cabling

3.3.3.4.1 Wiring

3.3.3.4.2 Shielding

3.3.3.4.3 Containment

3.3.3.4.4 Insulation

3.3.3.4.5 Clearance

3.3.3.4.6 Welding

3.3.3.5 Fabrication

3.3.4 Interchangeability

3.3.5 Safety

3.3.5.1 Personnel Safety

3.3.5.2 Electrical Safety

3.3.5.3 Electrical Connectors

3.3.5.4 Mechanical

3.3.5.5 Factors of Safety

3.3.5.5.1 Yield

3.3.5.5.2 Ultimate

3.3.5.6 Environmental Compliance

3.3.5.6.1 Environmental Compliance

3.3.5.6.2 Hexavalent Chrome

3.3.5.7 Toxic Product Safety

3.3.6 Human Performance/Human Engineering

3.3.6.1 Anthropometry

3.3.6.2 Equipment Handling

3.3.6.3 Labels

4 QUALITY ASSURANCE PROVISIONS

4.1 General

4.1.1 Quality Conformance Definitions

4.1.1.1 Inspection (I)

4.1.1.2 Analysis (A)

4.1.1.3 Demonstration (D)

4.1.1.4 Test (T)

5 PREPARATION FOR DELIVERY

6 NOTES

6.1 Intended Use

6.2 Definitions

6.3 Acronym list

6.4 Tables

3.2.1.1.7 Linear Displacement Sample Rate

3.2.1.1.8 In-line Force Sample Rate

3.2.1.1.9 Pneumatic Pressure Sample Rate

3.2.1.1.10 Pneumatic Pressure

7 Reserved

8 Reserved

9 Reserved

10 APPENDIX I

11 APPENDIX II: Testing – Shock Isolators

11.1 LCC Shock Isolator

11.1.1 Equilibrium Calibration Pressure Test

11.1.2 Pressure Differential Calibration Test

11.1.3 Piston Rod Seal Friction Calibration Test

11.1.4 Dynamic Performance Test

11.1.5 LCC SI Test Design Characteristics Summary

11.2 MSS Shock Isolator

11.2.1 Spring Rate Test

11.2.2 Damping Test

11.2.3 Friction Test

11.2.4 MSS SI Test Design Characteristics Summary

11.3 LER Shock Isolator

11.3.1 Static Load, Spring Rate Conformance, and Friction Conformance Test

a. Spring Rate Conformance

b. Break Away and Friction Force

c. Spring Rate and Friction

11.3.2 LER SI Test Design Characteristics Summary

List of Figures Figure 1. LCC SI Testing Diagrams – Equilibrium and Differential (Left), Dynamic (Right)

Figure 2. MSS SI Testing Diagrams – Spring Rate and Friction (Left), Damping (Right)

Figure 3. LER SI Testing Diagram – Spring Rate and Friction

Figure 4. Shock Isolator General Dimensions

Figure 5. LCC SI Dynamic Performance Test Schematic

Figure 6. LCC SI Dynamic Performance Acceptance Test Requirement

Figure 7. MSS Spring Rate Deflection Characteristics

Figure 8. MSS Allowable Damping Envelope

Figure 9. MSS Allowable Friction Envelope

Figure 10. LER SI Load-Stroke Curve Spring Rate and Friction Test

Figure 11. LER SI Load - Stroke Envelope - 12,000 lb Static Load

Figure 12. LER SI Load Stroke Envelope

List of Tables Table 1. Government Furnished Property List

Table 2. Definitions

Table 3 - Verification Requirement Compliance Matrix (VRCM)

Table 4. LCC SI Test Design Characteristics

Table 5. MSS SI Test Design Characteristics

Table 6. LER SI Test Design Characteristics

1. SCOPE

This document establishes the performance, design, development, and test requirements for the ICBM Shock Isolator Test Tower (SITT). The SITT provides means to mechanically validate Acceptance Test Plan (ATP) procedures for new and refurbished Missile Suspension System (MSS), Launcher Equipment Room (LER), and Launch Control Center (LCC) shock isolators.

1.1 Document overview

Section 1 General scope information, system overview, and defines the document contents and format.

Section 2 Identifies applicable documents that are referenced in this specification.

Section 3 Requirements for the system/subsystem.

Section 4 Verification requirements including the Verification Requirement Compliance

Matrix (VRCM).

Section 5 Traceability table that traces the requirements in this specification to the source requirements.

Section 6 Notes Section 7 Appendices

1.2 Document Structure and Format

In the document text, figures and tables are referenced by title. Refer to the List of Figures and List of Tables for the page location.

2 APPLICABLE DOCUMENTS

The following documents of the exact revision and date shown form a part of this specification to the extent specified herein. In the event of conflict between the documents referenced herein and the contents of this specification, the contents of this specification shall be considered a superseding requirement.

2.1 Government Documents

S-133-128D Minuteman Weapons System Specification

S-133-10763 Launcher Equipment Room Shock Isolated Floor

S-133-10764 Support – Missile, Shock Isolation and Alignment

S-133-112-1-56 Model Specification, Shock Isolator

FED-STD-595C Colors Used In Government Procurement 16 January 2008

DoD 5200.1-R Information Security Program January 1997

DoD 5200.2-R Personnel Security Program 23 February 1996

DODI # 8320.04 Item Unique Identification (IUID) Standards for Tangible Personal Property 3

September 2015

MIL-PRF-28800F General Specification for Test Equipment for use with Electrical and Electronic Equipment 24 June 1996

MMPDS-10 Metallic Materials Properties Development and Standardization (MMPDS) April 2015

MIL-HDBK-454B Electronic Guidelines 15 April 2007

MIL-STD-130N Identification Marking of U.S. Military Property 16 November 2012

MIL-STD-31000 Technical Data Packages 26 February 2013

MIL-STD-810G Environmental Engineering Considerations and Laboratory Tests 15 April 2014

MIL-STD-882E Standard Practice for System Safety 11 May 2012

MIL-STD-889B Dissimilar Metals 17 May 1993

MIL-STD-1472G Human Engineering 11 January 2012

MIL-STD-1568D Materials and Processes for Corrosion Prevention and Control in Aerospace Weapon Systems 31 August 2015

MIL-STD-7179A Finishes, Coatings, and Sealants, for the protection of Aerospace Weapon Systems 15 May 2014

MIL-STD-1546B Parts, Materials, and Processes Control Program for Space and Launch Vehicle 27 July 1992

MIL-STD-3018 Parts Management 2 June 2015

MIL-STD-461F Control of Electromagnetic Interference 10 December 2007

AFI 36-2101 Classifying Military Personnel 25 June 2013

AFI 32-1065 Grounding Systems 01 October 1998

AFI 63-101/20-101 Integrated Life Cycle Management 07 March 2013

AFI 91-101 Air Force Nuclear Weapons Surety Program 9 April 2015

AFI 91-102 Nuclear Weapon System Safety Studies, Operational Safety Reviews, and Safety Rules 25 February 2014

AFI 91-203 Air Force Consolidated Occupational Safety Instruction 17 September 2015

OSHA 1910.212 General Requirements for All Machines

OSHA 1925 Safety and Health Standards for Federal Service Contracts

OSHA 1910.27 Fixed Ladders (if applicable to design)

OSHA 1950,

Subpart 5

Electrical Safety

OSHA 1910.23 Guarding Floor and Wall Openings and Holes

AFOSH AFI 91-

203 (18.5.2.19)

Air Force Consolidated Occupational Safety Instruction 17 September 2015 (Pneumatic and Hydraulic Systems )

2.2 Non-Government Document

2.2.1 Specifications

AWS D1.1/D1.1M Structural Welding Code 1 January 2015

S9074-AQ-GIB-

010/248

Requirements for Welding and Brazing Procedure and Performance Qualification 1 August 1995

NFPA 70 National Electric Code 1 January 2014

29 CFR PART

Occupational Safety and Health Standards 1 July 2015

48 CFR 223.73 Minimizing the Use of Materials Containing Hexavalent Chromium 5 May 2011

2.2.2 Drawings

25-66751 LER Shock Isolator

25-66608 MSS Shock Isolator

1269B-2000 LCC Shock Isolator W3/5

25-37556 LCC Shock Isolator W1

3 REQUIREMENTS

3.1 Definition

The Shock Isolator Test Tower (SITT) validates the operating parameters of the Missile Suspension System (MSS), Launch Control Center (LCC), and Launcher Equipment Room (LER) Shock Isolators (SI) In Accordance With (IAW) their respective acceptance criteria.

3.1.1 System Diagrams

Shock isolator test tower test diagrams are provided in Figure 1, Figure 2 and Figure 3.

Figure 1. LCC SI Testing Diagrams – Equilibrium and Differential (Left), Dynamic (Right)

Figure 2. MSS SI Testing Diagrams – Spring Rate and Friction (Left), Damping (Right)

Figure 3. LER SI Testing Diagram – Spring Rate and Friction

3.1.2 Interface Definition

3.1.2.1 MSS Shock Isolator

3.1.2.1.1 Hydraulic and Mechanical Interface

a. The SITT shall mechanically interface with the MSS SI in a way representative of the installed configuration with the piston eyelet end on top.

b. The SITT shall provide means to interface the MSS SI with a TBD hydraulic pump while installed in the test tower.

3.1.2.2 LER Shock Isolator

3.1.2.2.1 Hydraulic and Mechanical Interface

a. The SITT shall mechanically interface with the LER SI in a way representative of the installed configuration with the piston eyelet end on top.

b. The SITT shall provide means to interface the LER SI with a TBD hydraulic pump while installed in the test tower.

3.1.2.3 LCC Shock Isolator

3.1.2.3.1 Pneumatic and Mechanical Interface

a. The SITT shall mechanically interface with the LCC SI in a way representative of the installed configuration with the piston eyelet end on top.

b. The SITT shall provide means to interface the LER SI with a TBD air compressor while installed in the test tower.

3.1.2.5 SITT External Interface Requirements

N/A

3.1.3 Government Furnished Property List

The government furnished property list includes equipment that will be provided at the final installation location for test tower qualification and acceptance.

Table 1. Government Furnished Property List

Index Property Part Number Category 5 MSS SI QTP/ATP Only 6 LER SI QTP/ATP Only 7 LCC SI W1 QTP/ATP Only 8 LCC SI W3/5 QTP/ATP Only

3.1.4 Government Loaned Property List

Reserved

3.2 Characteristics

3.2.1 Performance Characteristics

The following performance criteria are applicable to the SITT:

3.2.1.1 Testing – General Characteristics

3.2.1.1.1 SI Test Position

The SITT shall hold all SIs in vertical position with piston eyelet end on top.

3.2.1.1.2 Stroke

The SITT shall allow the piston rods a minimum of 54 inches travel.

3.2.1.1.3 Extend/Retract Rate

The SITT shall be able to extend/retract piston rods at a rate between 0.2 and 1.0 inches/sec.

3.2.1.1.4 Hold Position

The SITT shall be able to hold piston rods in place at any 1/4 inch maximum increment within the specified stroke.

3.2.1.1.5 Max Forces, Scenario 1

The SITT shall have the ability to support 19,000 ± 500 lb (static) and also use the LCC SI to arrest a 19,000 lb object accelerating, from stand-still, at 32ft/s2 for 2 inches.

3.2.1.1.6 Max Forces, Scenario 2

The SITT shall have the ability to support 41,000 ± 500 lb (static) and also use the MSS SI to arrest a 41,000 lb object accelerating, from stand-still, at 32ft/s2 for 28.015 inches.

3.2.1.1.7 Linear Displacement Data Recording

The SITT shall record linear displacement of piston rods at minimum sample rate of 50 Hz for the entirety of the stroke with minimum resolution of ±0.25in.

3.2.1.1.8 In-line Force Data Recording

The SITT shall record in-line force at minimum sample rate of 50 Hz for forces between 0 and 64,000 lbf with minimum resolution of ± 0.5lbf.

3.2.1.1.9 Pneumatic Pressure Data Recording

The SITT shall independently record pneumatic pressure for the LCC SI tank and cylinder at minimum sample rate of 50 Hz for pressures between 0 and 600psig with a minimum resolution of ±0.5psig.

3.2.1.1.10 Pneumatic Pressure

The SITT shall pneumatically pressurize and bleed pressure from LCC SI up to 500 psi using provided or included compressed air and have the ability to manipulate pressures independently between the cylinder and tank of the LCC SI.

3.2.1.2 Testing – Applied Forces

3.2.1.2.1 LCC Shock Isolator

The SITT shall be able to apply a force equal to a 19,000 ± 500lbf object accelerating at 32.2 ft/s2 to the LCC SI, with that object having first accelerated 2.0 ± 0.1in prior to being arrested by the

SI.

3.2.1.2.2 MSS Shock Isolator

The SITT shall be able to apply a force equal to a 41,000 ± 500lbf object accelerating at 32.2 ft/s2 to the MSS SI.

3.2.1.2.3 LER Shock Isolator

The SITT shall be able to apply 12,000lbf to the LER SI.

3.2.2 Physical Characteristics

3.2.2.1 ESD

The test equipment containing electrical and/or electronic subsystems shall be evaluated for ESD by testing in accordance with the test method described in S-133-128D Appendix II Paragraph 20.4.

3.2.2.2 Size

N/A

3.2.2.3 Weight

N/A

3.2.3 Reliability

3.2.3.1 Availability/Reliability

N/A

3.2.3.2 Operating Life

N/A

3.2.4 Maintainability

3.2.4.1 Preventative Maintenance

N/A

3.2.4.2 Calibration

N/A

3.2.4.3 Accessibility for maintenance

N/A

3.2.4.4 Mean Time To Repair

N/A

3.2.4.5 Maintenance and calibration aids

N/A

3.2.4.6 Accessibility for repair and adjustment

N/A

3.2.4.7 Accessibility for adjustment/calibration

N/A

3.2.5 Environmental Conditions

3.2.5.1 Operating

The SITT and its components shall meet the requirements of this specification after exposure to operating environmental conditions specified in Appendix II of Specification S-133-128, unless otherwise specified by the procurement agency.

3.2.5.1.1 Temperature

The SITT shall be operated in an indoor, controlled environment. The SITT shall be constructed to withstand operating temperature range between +50 to +90 °F.

3.2.5.1.2 Humidity

The SITT shall operate in an indoor, controlled environment that has a RH range of 20% to 80% ± 5% with maximum dew point temperature of 65°.

3.2.5.1.3 Altitude

Between sea level and 6500 feet, which is equivalent to 14.7 to 11.6 psia.

3.2.5.1.4 Fungus

An analysis of design documentation shall be performed to verify that the materials listed in MIL- STD-810 Method 508.6 Annex B, Group II are not used in the design of the test equipment. If the analysis does not show compliance, a test shall be performed in accordance with MIL-STD-810 Method 508.6, based on a cost benefit analysis decision by the ICBM Systems Directorate Chief Engineer.

3.2.5.1.5 Wind

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.6 Rain

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.7 Snow

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.8 Hail

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.9 Ice

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.10 Salt

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.11 Dust

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.12 Sunshine

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.13 Vibration

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.1.14 Shock

N/A. The SITT shall be operated in an indoor, controlled environment.

3.2.5.2 Non-Operating

Non-operational environments or transportation requirements do not apply per S-133-128D Appendix II.

3.2.5.2.1 Temperature

N/A per S-133-128D Appendix II.

3.2.5.2.2 Humidity

N/A per S-133-128D Appendix II.

3.2.5.2.3 Altitude

N/A per S-133-128D Appendix II.

3.2.5.2.4 Fungus

N/A per S-133-128D Appendix II.

3.2.5.2.5 Wind

N/A per S-133-128D Appendix II.

3.2.5.2.6 Rain

N/A per S-133-128D Appendix II.

3.2.5.2.7 Snow

N/A per S-133-128D Appendix II.

3.2.5.2.8 Hail

N/A per S-133-128D Appendix II.

3.2.5.2.9 Ice

N/A per S-133-128D Appendix II.

3.2.5.2.10 Salt

N/A per S-133-128D Appendix II.

3.2.5.2.11 Dust

N/A per S-133-128D Appendix II.

3.2.5.2.12 Sunshine

N/A per S-133-128D Appendix II.

3.2.5.2.13 Vibration

N/A per S-133-128D Appendix II.

3.2.5.2.14 Shock

N/A per S-133-128D Appendix II.

3.2.6 Transportability

N/A. The SITT will be assembled on site.

3.2.7 Implementation

The following requirements are fabrication specifications only based on the current implementation and will only be demonstrated during ATP:

3.2.7.1 Firmware

If the design includes firmware, the test set user interface shall provide the operator a means to confirm a CPIN number upon power up.

3.2.7.2 Test Set Operation

a. The test set shall allow the operator to set the date and time.

b. The test set shall utilize a single cable and a series of adapters to interface to the defined

UUTs.

c. The test set shall allow the operator to manually enter information and allow the operator to view the information entered via a display.

d. The test set shall allow the operator to adjust the intensity of the display backlight.

3.2.7.3 Calibration

The test set calibration shall only be performed by the contractor or PMEL.

3.2.7.4 Visual Displays

The test set display shall provide prompts to guide the operator through the various test set operations.

3.3 Design and Construction

3.3.1 Materials

3.1.1.1 Materials, Processes, and Parts

a. Materials and processes shall be selected in the order of precedence specified in MIL-

STD-1546

b. Parts selection in accordance with MIL-STD-3018 unless otherwise specified herein or in an individual item specification

c. Common Materials Specification (MS), Army/Navy (A/N), or National Aerospace

Standard (NAS) mechanical parts shall be used in preference to similar commercial items.

3.3.1.2 Toxic Products and Formulation

Any toxic materials used shall be approved by the procuring activity.

3.3.1.3 Corrosion Prevention and Control

Corrosion prevention and control shall meet requirements in MIL-STD-1568. Commercial parts shall conform to selected manufacturers standard processes.

3.3.1.4 Dissimilar Metals

Contact between dissimilar metals, as defined in MIL-STD-889, shall be avoided. Where unavoidable, contact surfaces shall be protected against galvanic corrosion as specified in MIL- STD-889. Contacts between aluminum and copper or their alloys or any other deviations shall not be used without prior approval of the procuring activity.

3.3.1.5 Electromagnetic Interference Characteristics

The SITT shall comply with the EMI/ESD requirements stated in the WSS and/or MIL-STD- 461F.

3.3.1.6 Finish

The commercial components may have the as-purchased original finish and colors, provided that such finishes and colors will withstand the environments as specified herein. Commercial parts which must be refinished to withstand the specified environmental conditions shall be refinished to requirements of MIL-STD-1568.

3.3.2 Nameplates and Product Markings

a. Nameplates, product marking, serial and lot number marking, and all other identifying marking required for the system and its equipment and parts shall be in accordance with

MIL-STD-130.

b. The top assembly test equipment shall have a nameplate and product marking IAW MIL- STD-130, Construct Two.

c. The labels shall be placed in an area that is easily viewable to the end user.

d. Any subassembly of the test equipment that meets the criteria of DODI #8320.04 paragraphs 5.3.1 through 5.3.4 shall also be marked IAW MIL-STD-130, Construct Two.

Parts within an assembly or a subassembly not normally subject to removal, replacement, or repair, need not be marked.

3.3.2.1 Labels

a. Information and warning labels that are not part of the equipment or unit shall be securely attached to prevent its loss, damage, slippage, or accidental or unauthorized removal.

b. The location of any information or warning label not part of the test equipment shall be attached to a structural member that is not removed during equipment servicing or routine maintenance.

c. All labels shall be mounted so as to minimize wear or obscuration by grease, grime, or dirt.

d. To meet the label requirements herein, the labels may be etched directly onto the test equipment.

e. The test equipment shall be appropriately and clearly labeled.

f. Special labels such as warning and instructions shall be prominently displayed in proximity to their intended use.

g. Weight, lifting points, test and service points shall be labeled per the label requirements herein.

3.3.3 Workmanship

3.3.3.1 Cleaning

After fabrication, parts and assembled equipment shall be cleaned of smudges, loose, spattered, or excess solder, weld metal, metal chips and mold release agents, or any other foreign material which might detract from the intended operation, function, or appearance of the equipment.

3.3.3.2 Threaded Parts

Screws, nuts, and bolts shall show no evidence of cross threading, mutilation, or detrimental or hazardous burrs, and have the proper torque per the specification drawing.

3.3.3.3 Bearing Assemblies

a. Bearing assemblies shall be free of rust, discoloration, and imperfections of ground, honed, or lapped surfaces.

b. Contacting surfaces shall be free of tool marks, gouge marks, nicks, or other surface type defects.

c. There shall be no detrimental interference, binding, or galling.

3.3.3.4 Cabling

All internal and external wire harness and cables used for the test equipment shall comply with the following as applicable:

3.3.3.4.1 Wiring

Wires and cables shall be positioned or protected to avoid contact with rough or irregular surfaces and sharp edges and to avoid damage to conductors or adjacent parts.

3.3.3.4.2 Shielding

a. Shielding on wires and cables shall be secured in a manner that will prevent it from contacting or shorting exposed current-carrying parts.

b. The ends of the shielding or braid shall be secured to prevent fraying.

3.3.3.4.3 Containment

a. The harness and cable from containment means shall be neat in appearance, uniformly applied, and positioned to retain critical form factors and breakout locations.

b. The containment means, (lacing, ties, tie down straps, etc.) shall not cause the wire or cable insulation to deform so that performance characteristics are adversely affected.

3.3.3.4.4 Insulation

There shall be no evidence of burns, abrading, or pinch marks in the insulation that could cause short circuits or leakage.

3.3.3.4.5 Clearance

The clearance between wires or cables and heat generating parts shall be sufficient to minimize deterioration of the wires or cables.

3.3.3.4.6 Welding

All welds shall be free of defects, having uniform and smooth fillets, no burn-through, and no damage to adjacent parts resulting from the welding.

3.3.3.5 Fabrication

a. The test equipment shall be fabricated and finished skillfully using standard shop practices and procedures.

b. Particular attention shall be given to: freedom from blemishes, defects, burrs, and sharp edges, marking of parts, appearance of soldering, broaching, welding, riveting, painting and wiring, alignment of parts, and tightness of threaded fasteners.

3.3.4 Interchangeability

a. Design tolerances shall permit parts, subassemblies, and assemblies to be used in their parent assemblies without regard to the source of supply or manufacturer.

b. Parts, subassemblies, and assemblies having the full range of dimensions and characteristics permitted by the specification governing the part, subassembly, or assembly shall be usable as replacement items without selection and without departure from the specified performance guidelines of the parent items.

c. During the standard design review cycle as identified by the respective design authority, all non-military standard parts shall be identified to the customer.

3.3.5 Safety

3.3.5.1 Personnel Safety

The test equipment design and operation shall follow the order of precedence established in MIL- STD-882, section 4.4, for mitigating system hazards.

a. The test equipment shall comply with MIL-STD-1472 section 4.8, Safety.

b. The test equipment shall comply with MIL-STD-1472, sections 5.8.2.2, Display Lighting, and 5.8.3.2, Hazardous Noise.

c. The test equipment shall comply with MIL-STD-1472, section 5.13 Hazards and Safety, sub sections 5.13.2.1, 5.13.2.6, 5.13.4.6, 5.13.5.4, 5.13.7.1.2 - 5.13.7.1.5, 5.13.7.4.1, & 5.13.7.5.

d. The test equipment should comply with MIL-STD-1472, Section 5.1 Control-display integration, paragraphs 5.1.1 - 5.1.1.6 & 5.1.5.

e. Use MIL-STD-1472 as a guide with particular emphasis in the following paragraphs and their sub-paragraphs:

a. Section 5.2 Visual displays.

b. Section 5.4 Controls.

c. Section 5.9 Design for the maintainer.

f. Electrical design guidelines for personnel safety are in MIL-HDBK-454, Guideline 1 and should be applied where feasible.

g. As applicable, guidelines for safety markings are provided in MIL-HDBK-454, Guideline 1 section 4.8 and should be applied where feasible.

3.3.5.2 Electrical Safety

a. The test equipment should meet the applicable requirements of the National Electrical

Code NFPA 70 and 29 CFR 1910 - Subpart S - Electrical.

b. All electrical conductors shall be protected against condensate by location or insulation.

c. Uninsulated energized connections shall be located or covered so that accidental contact or grounding is prevented.

d. All metallic surfaces shall be bonded together such that the ground terminal of the AC power plug provides grounding of all conductive structural parts and enclosures.

e. All other external components shall be at ground potential.

3.3.5.3 Electrical Connectors

a. Electrical connectors shall be selected or arranged so that it is physically possible to connect only the correct electrical cable and prevent improper connection.

b. This physical means to prevent improper connection shall be accomplished by providing keys or aligning pins, or size, location, or type differences, or equivalent means.

c. All electrical connectors shall be clearly labeled at least once such that the labels are on the cable near the connector or on the connector itself.

3.3.5.4 Mechanical

a. Glass fiber materials shall not be used as outer covering on cables, wires, or other components where they may cause skin irritation to personnel.

b. Hinged devices with hazardous characteristics shall be avoided.

3.3.5.5 Factors of Safety

All hardware which forms a part of the unit structure shall be designed for the following minimum factors of safety:

3.3.5.5.1 Yield

All hardware that forms a part shall be designed for simultaneous application of the limit load, times the yield factor of safety specified herein, and the accompanying environments for each design condition without experiencing detrimental deformation or stress above the structural material yield strength.

a. The minimum yield factor of safety for long-term static and maintenance loads shall be 1.65.

b. The minimum yield factor of safety for lifting loads shall be 3.0.

c. The minimum yield factor of safety for pressure vessels and lines that experience operating pressure surges shall be 1.65.

3.3.5.5.2 Ultimate

All hardware that forms a part shall be designed for simultaneous application of the limit load, times the ultimate factor of safety specified herein, and the accompanying environments for each design condition without experiencing stress above the material ultimate strength.

a. The minimum ultimate factor of safety for long-term static and maintenance loads shall be 2.0.

b. The minimum ultimate factor of safety for lifting loads shall be 5.0.

c. The minimum ultimate factor of safety for pressure vessels and lines that experience operating pressure surges shall be 5.0.

3.3.5.6 Environmental Compliance

3.3.5.6.1 Environmental Compliance

The production, design, and maintenance of the end item shall not require the use of Class I or II Ozone Depleting Substances (ODS), Polychlorinated Biphenyls (PCB), or asbestos; and shall minimize the use of hazardous materials including Environmental Protection Agency (EPA) 17 materials and Hazardous Air Pollutants. The production, design, and maintenance must be in compliance with federal, state, and local environmental laws and regulations.

3.3.5.6.2 Hexavalent Chrome

The use of Hexavalent Chrome (Cr6+), unless excluded by 48 CFR 223 or approved by the PEO or ALC/CC, shall be prohibited in the design and maintenance of the end item.

3.3.5.7 Toxic Product Safety

a. Test equipment materials shall not liberate gases which alone, or when combined with the atmosphere, result in corrosive fumes which would be detrimental to the test equipment the Unit Under Test (UUT), or to the health of personnel.

b. The hazmat program shall identify toxic or carcinogenic materials in the test set designs using the EPA-17 screening list.

3.3.6 Human Performance/Human Engineering

3.3.6.1 Anthropometry

Maintenance access and workspace should be in accordance with MIL-STD-1472, sections 5.9.9 for access openings and cover designs and 5.7.1.3 and 5.7.2 for workspace design.

3.3.6.2 Equipment Handling

The test equipment shall have a means for grasping, handling and carrying in accordance with weight requirements within MIL-STD-1472 section 5.9.11.3 and 5.9.11.5.1.

3.3.6.3 Labels

The SITT and its components shall be appropriately and clearly labeled where required. Labels shall include weight, lift points, test and service points. Special labels such as warnings and instructions shall be prominently displayed in close proximity to their intended use.

4 QUALITY ASSURANCE PROVISIONS

4.1 General

Inspections which consist of examinations, demonstrations, tests, and analyses shall be conducted during the design and development of the SITT to provide the Air Force with assurance of compliance with the requirements of this specification.

The contractor shall be responsible for the performance of all inspections for the SITT produced in accordance with this specification. The procuring activity reserves the right to perform any of the specified inspections at the contractor’s or other facilities.

Qualification of the SITT to assure compliance with the requirements of Section 3 shall be by examinations, demonstrations, tests, or analyses, defined as follows:

4.1.1 Quality Conformance Definitions

4.1.1.1 Inspection (I)

Inspection, sometimes referred to as Examination, consists of visual inspection, physical manipulation, weighing and/or measurements to verify that a configuration item conforms to the design requirements. This verification method also includes a review of the documentation that controls the configuration.

4.1.1.2 Analysis (A)

Analysis is defined as a computational method using test data or modeling to verify the performance. Analysis is a technical evaluation of equations, graphs, reduced data, and/or representative data. All analysis methods should be standardized or industry recognized methods..

Analysis tools need to be under configuration control and approved by the quality organization.

Verification by analysis is used when it is not feasible to perform tests to obtain the required data.

Analysis is also used where testing is not warranted for verification of requirements.

4.1.1.3 Demonstration (D)

Demonstration is a simple, uninstrumented, buyer-witnessed test where success is determined by a "GO" or "NO-GO" result. These verifications will not generally involve any significant use of analysis or test equipment. In addition, these are verifications that are generally done only once.

An example might be the requirement that a radar target of a certain type have a diamond shape displayed in red on the cockpit display. This could be demonstrated on a system bench using a target generator. Once visually confirmed, this requirement is satisfied and would in all probability not be repeated.

4.1.1.4 Test (T)

In the context of a verification method, test implies a formal process. Test is the verification that a requirement is met by a thorough exercising of the system/subsystem/item. This includes actual measurement of unit performance with calculations/analysis as required and under a controlled and/or recorded environment.

5 PREPARATION FOR DELIVERY

N/A

6 NOTES

6.1 Intended Use

The SITT will be used to verify adherence to respective SI acceptance testing.

6.2 Definitions

Table 2. Definitions

Yield Strength Yield strength (stress) is the stress at which a structural material exhibits a 0.2 percent permanent deformation.

Ultimate strength Ultimate strength (stress) is the maximum stress, which a structural material exhibits prior to material rupture or other failure mechanism of the material.

Factor of safety The factor of safety is an arbitrary factor intended to account for slight variations from item to item in fabrication quality and details, internal load distribution within the structure, and possible degradation in strength that may result from the actual history of treatment of each structural item in service.

Operating environments Operating environments are those environments to which equipment is exposed while performing its operational functions or while in a state of readiness for performing those functions.

Non-operating environments Non-operating environments are those environments other than operating environments, including shipping, handling and storage.

Normal Position The normal position refers to when the LCC shock isolator piston rod is extended 34 inches.

Piston Equilibrium Pressure (LCC SI) The pressure at which the LCC shock isolator cylinder and tank pressures are stable when a 19,000 (+/- 500) lb weight is suspended from the shock isolator.

Shock Isolator Equilibrium (LCC SI) LCC shock isolator equilibrium occurs when the cylinder and tank pressures have stabilized and the piston has stopped moving.

Deadband An interval of a signal domain or band where no action occurs

Shock Isolator Static Position (LER SI) The LER SI is in its static position when 21 inches of the piston rod is extended.

6.3 Acronym list

Acronym Definition ± plus/minus °C Degrees Celsius °F Degrees Fahrenheit AFB Air Force Base AF Air Force AFI Air Force Instruction ANSI American National Standards Institute ATP Acceptance Test Procedure ATR Acceptance Test Report COTS Commercial Off The Shelf CPIN Computer Program Identification Number dB Decibel DoD Department of Defense DoDD Department of Defense Directive ESD Electro Static Discharge EPA Environmental Protection Agency FCA Functional Configuration Audit fpm Feet per minute fps Feet per second ft Feet GFP Government Furnished Property GTP General Test Plan HAFB Hill Air Force Base Hz Hertz IAW In Accordance With ICBM Intercontinental Ballistic Missile lb Pounds lbf Pounds force m Meter ms Milliseconds MSE Maintenance Support Equipment ODS Ozone Depleting Substances PCA Physical Configuration Audit psig Pounds per square inch, gauge QTP Qualification Test Procedure SAE Society of Automotive Engineers TBD To be Determined U.S. United States UUT Unit Under Test USAF United States Air Force VRCM Verification Requirement Compliance Matrix

6.4 Tables

Table 3 - Verification Requirement Compliance Matrix (VRCM)

Table 6. Quality Conformance Cross Reference Matrix

Paragraph

Conformance and Verification Methods

N ot

A p p li ca b le

E xa m in at io n

D em on st ra ti on

T es t

A n al ys is

Q u al if ic at

A cc ep ta ce

3.1.2 Interface Definition X

3.1.2.1 MSS Shock Isolator X

3.1.2.1.1 Hydraulic and Mechanical Interface X X X

3.1.2.2 LER Shock Isolator X

3.1.2.2.1 Hydraulic and Mechanical Interface X X X

3.1.2.3 LCC Shock Isolator X

3.1.2.3.1 Pneumatic and Mechanical Interface X X X

3.1.2.5 SITT External Interface Requirements X X X

3.2.1 Performance Characteristics X

3.2.1.1 Testing – General Characteristics X

3.2.1.1.1 SI Test Position X X

3.2.1.1.2 Stroke X X

3.2.1.1.3 Extend/Retract Rate X X

3.2.1.1.4 Hold Position X X

3.2.1.1.5 Max Forces, Scenario 1 X X

3.2.1.1.6 Max Forces, Scenario 2 X X

3.2.1.1.7 Linear Displacement Sample Rate X X

3.2.1.1.8 In-line Force Sample Rate X X

3.2.1.1.9 Pneumatic Pressure Sample Rate X X

3.2.1.1.10 Pneumatic Pressure X X

3.2.1.2 Testing – Applied Forces X

3.2.1.2.1 LCC Shock Isolator X

3.2.1.2.2 MSS Shock Isolator X

3.2.1.2.3 LER Shock Isolator X

3.2.2 Physical Characteristics X

3.2.2.1 ESD X X

3.2.2.2 Size X X

Table 6. Quality Conformance Cross Reference Matrix

Paragraph

Conformance and Verification Methods

N ot

A p p li ca m in at on st ra t

A n al al if ic at ep ta

3.2.2.3 Weight X X

3.2.3 Reliability X

3.2.3.1 Availability/Reliability X

3.2.3.2 Operating Life X

3.2.4 Maintainability X

3.2.4.1 Preventative Maintenance X

3.2.4.2 Calibration X

3.2.4.3 Accessibility for maintenance X

3.2.4.4 Mean Time To Repair X

3.2.4.5 Maintenance and calibration aids X

3.2.4.6 Accessibility for repair and adjustment X

3.2.4.7 Accessibility for adjustment/calibration X

3.2.5 Environmental Conditions X

3.2.5.1 Operating X

3.2.5.1.1 Temperature X X

3.2.5.1.2 Humidity X X

3.2.5.1.3 Altitude X X

3.2.5.1.4 Fungus X X

3.2.5.1.5 Wind X

3.2.5.1.6 Rain X

3.2.5.1.7 Snow X

3.2.5.1.8 Hail X

3.2.5.1.9 Ice X

3.2.5.1.10 Salt X

3.2.5.1.11 Dust X

3.2.5.1.12 Sunshine X

3.2.5.1.13 Vibration X

3.2.5.1.14 Shock X

3.2.5.2 Non-Operating X

3.2.5.2.1 Temperature X

Conformance and Verification Methods

N ot

A p p li ca m in at on st ra t

A n al al if ic at ep ta

3.2.5.2.2 Humidity X

3.2.5.2.3 Altitude X

3.2.5.2.4 Fungus X

3.2.5.2.5 Wind X

3.2.5.2.6 Rain X

3.2.5.2.7 Snow X

3.2.5.2.8 Hail X

3.2.5.2.9 Ice X

3.2.5.2.10 Salt X

3.2.5.2.11 Dust X

3.2.5.2.12 Sunshine X

3.2.5.2.13 Vibration X

3.2.5.2.14 Shock X

3.2.6 Transportability X

3.2.7 Implementation X

3.2.7.1 Firmware X X X

3.2.7.2 Test Set Operation X X

3.2.7.3 Calibration X X

3.2.7.4 Visual Displays X X

3.3 Design and Construction X

3.3.1 Materials X

3.1.1.1 Materials, Processes, and Parts X X

3.3.1.2 Toxic Products and Formulation X X

3.3.1.3 Corrosion Prevention and Control X X

3.3.1.4 Dissimilar Metals X X

3.3.1.5 Electromagnetic Interference Characteristics X X

3.3.1.6 Finish X X

3.3.2 Nameplates and Product Markings X X

3.3.2.1 Labels X X

3.3.3 Workmanship X

Conformance and Verification Methods

N ot

A p p li ca m in at on st ra t

A n al al if ic at ep ta

3.3.3.1 Cleaning X X X

3.3.3.2 Threaded Parts X X

3.3.3.3 Bearing Assemblies X X

3.3.3.4 Cabling X X

3.3.3.4.1 Wiring X X

3.3.3.4.2 Shielding X X

3.3.3.4.3 Containment X X

3.3.3.4.4 Insulation X X

3.3.3.4.5 Clearance X X

3.3.3.4.6 Welding X X

3.3.3.5 Fabrication X X

3.3.4 Interchangeability X X

3.3.5 Safety X

3.3.5.1 Personnel Safety X X

3.3.5.2 Electrical Safety X X

3.3.5.3 Electrical Connectors X X

3.3.5.4 Mechanical X X

3.3.5.5 Factors of Safety X

3.3.5.5.1 Yield X X

3.3.5.5.2 Ultimate X X

3.3.5.6 Environmental Compliance X X

3.3.5.6.1 Environmental Compliance X X

3.3.5.6.2 Hexavalent Chrome X X

3.3.5.7 Toxic Product Safety X X

3.3.6 Human Performance/Human Engineering X

3.3.6.1 Anthropometry X X

3.3.6.2 Equipment Handling X X

3.3.6.3 Labels X X

LCC SI Old Tower Comparison Test X X LER SI Old Tower Comparison Test X X

Conformance and Verification Methods

N ot

A p p li ca m in at on st ra t

A n al al if ic at ep ta

MSS SI Old Tower Comparison Test X X LCEB Old Tower Comparison Test X X

7 Reserved

8 Reserved

9 Reserved

10 APPENDIX I

Figure 4. Shock Isolator General Dimensions

11 APPENDIX II: Testing – Shock Isolators NOTE: This is provided for reference only and can be found in applicable documents listed in Section 2 herein.

11.1 LCC Shock Isolator

11.1.1 Equilibrium Calibration Pressure Test

With the piston in its normal position, and with 19,000 ± 500 lb suspended from the bottom fitting, adjust shock isolator pressure until piston equilibrium pressure is reached.

Piston equilibrium pressure shall be 420 ± 15 psig.

11.1.2 Pressure Differential Calibration Test

With the shock isolator at equilibrium, measure the pressure differential between the cylinder and pressure tank. The pressure differential between the cylinder and pressure tank shall not exceed 0.5 psig, with the greater pressure in the pressure tank.

11.1.3 Piston Rod Seal Friction Calibration Test

With the shock isolator at equilibrium, measure the change in pressure (due to static friction) required to start raising or lowering the test weight from the equilibrium position. The force required to move the piston in either direction from its equilibrium position against seal static friction shall not exceed 470 pounds (equivalent to 10 psig).

11.1.4 Dynamic Performance Test

Test the shock isolator in accordance with Figure 5. The shock isolator must arrest from 2 +/- 0.1 inches of free-fall. The data acquisition system must be capable of verifying the shock isolator meets the performance curve in Figure 6.

Figure 5. LCC SI Dynamic Performance Test Schematic

Figure 6. LCC SI Dynamic Performance Acceptance Test Requirement

11.1.5 LCC SI Test Design Characteristics Summary

Table 4. LCC SI Test Design Characteristics

Key: C – Cylinder Pressure, T – Tank Pressure, D – Piston Extension Distance Test Suspended

Weight (lb) Max Piston Travel (in)

Expected Piston Extension Position (in)

Measurement Special Comments

Equilibrium Calibration

19,000 +/-

54 34 ± 12 C, T, D Pressurize SI

Pressure Differential Calibration

19,000 +/-

54 34 ± 0.25 C, T, D Pressurize SI

Piston Rod Seal Friction Calibration

19,000 +/-

54 34 ± 0.25 C, T, D Pressurize SI

Dynamic Performance

19,000 +/-

54 26 ± 12 C, D Drop test SI and verify SI meets performance curve.

11.2 MSS Shock Isolator

11.2.1 Spring Rate Test

The spring rate of the liquid spring, when pressurized to 20,000 ± 200 psig with piston bottomed on the upper seal, shall be 910 pounds per inch ±5%. The spring rate shall be established by a straight line from the fully extended to the fully retracted position. The spring rate shall be within the limits specified in Figure 7.

Figure 7. MSS Spring Rate Deflection Characteristics

11.2.2 Damping Test

Liquid spring damping will fall within limits specified below in Figure 8. The spring is to be pressurized to 20,000 +200/-0 psig while supporting a weight of 41,000 ± 500 pounds. The weight is to be raised to the available stroke of the spring and released allowing the weight to fall.

Figure 8. MSS Allowable Damping Envelope

11.2.3 Friction Test

The liquid spring friction measured during the spring rate test shall not exceed 10% of the load required to bottom the piston on the upper seal.

Figure 9. MSS Allowable Friction Envelope

11.2.4 MSS SI Test Design Characteristics Summary

Table 5. MSS SI Test Design Characteristics

Key: P – SI Pressure, F – Force, D – Piston Extension Distance Test Suspended

Weight (lb) Max Piston Travel (in)

Measurement Special Comments

Spring Rate None 27.5 P, F, D Extend/retract piston Damping 41,000 ±

27.5 P, F, D Drop test SI and verify SI

meets performance curve Dynamic Response

None 27.5 P, F, D Fully extend piston and release

Friction None 27.5 P, F, D Extend/retract piston and verify SI meets performance curve

11.3 LER Shock Isolator

11.3.1 Static Load, Spring Rate Conformance, and Friction Conformance Test

a. Spring Rate Conformance Using the test fixture, cycle the isolator up 7 ± 0.25 inches and down 7 ± 0.25 inches (total piston travel of 14 ± 0.5 inches) from the static position for 5 complete cycles. The piston velocity shall be less than 1.0" per second. Measure and record the load/stroke data during extension and retraction. Calculate the linear spring rate as shown by Figure 10.

The recorded spring rate value at the static position shall equal 650 ± 65 pounds per inch when the isolator has a nominal static load of 12,000 pounds. The load stroke curve shall fall within the load-stroke envelope of Figure 10.

b. Break Away and Friction Force The sliding friction (within 2.5" of normal static position) shall not exceed 900 lbs. when loaded with a nominal static load of 12,000 lbs. The breakaway friction shall not be greater than 150% of the sliding friction.

i. From the preceding curve determine the maximum value of one-half the difference of the upper and lower traces at a point within ± 2.5 inches of the nominal static position. This value shall not exceed 900 pounds when the isolator has a nominal static load of 12,000 pounds.

ii. Determine the min-point curve of the friction deadband. The breakaway friction is calculated from the point where piston rod motion starts to the mid-point curve and this value shall not exceed 1,350 pounds.

c. Spring Rate and Friction The isolator shall provide a spring rate within the load - stroke envelope specified in Figure 12 for the following instructions:

i. Starting from the static position of 21 ± 0.25 inches of piston rod extension, extend the SI piston between 0.2 – 1.0 inches per second until the piston rod has extended 7 +0.5/-0 inches (total extension of 28 +0.5/-0 inches).

ii. Retract SI piston rod at a rate of between 0.2 – 1.0 inches per second until the isolator piston has retracted 7 +0.5/-0 inches below static position (total extension of 14 +0.5/-0 inches).

iii. Extend SI piston rod at a rate of between 0.2 – 1.0 inches per second until isolator piston has reached the initial static position (total extension of 21 ±

0.25 inches).

Figure 10. LER SI Load-Stroke Curve Spring Rate and Friction Test

Figure 11. LER SI Load - Stroke Envelope - 12,000 lb Static Load

Figure 12. LER SI Load Stroke Envelope

11.3.2 LER SI Test Design Characteristics Summary

Table 6. LER SI Test Design Characteristics

Key: P – SI Pressure, F – Force, D – Piston Extension Distance Test Suspended

Weight (lb) Max Piston Travel (in)

Measurement Special Comments

Static Load None 35.5 P, F, D Apply 12,000 lb load Spring Rate None 35.5 P, F, D Extend/retract piston Break Away and Friction Force

None 35.5 P, F, D Extend/retract piston

Spring Rate and Friction Test

None 35.5 P, F, D Extend/retract piston and verify SI meets performance curve