ALPHA MAGNETIC SPECTROMETER - 02 (AMS-02) EXPERIMENT/PAYLOAD INTEGRATION
HARDWARE (PIH) INTERFACES

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| Space and Life Sciences Directorate                                   |
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| Flight Projects Division                                              |
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| June, 2002                                                            |
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| ![](media/image1.wmf){width="0.9576388888888889in"                    |
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| National Aeronautics and                                              |
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| Space Administration                                                  |
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| **Lyndon B. Johnson Space Center**                                    |
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| Houston, Texas                                                        |
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**ALPHA MAGNETIC SPECTROMETER -- 02 (AMS-02) EXPERIMENT/PAYLOAD
INTEGRATION HARDWARE (PIH) INTERFACES**

**Prepared By:**

> T. K. MEHTA
>
> AMS PAYLOAD ENGINEER, LMSO

**Reviewed By:**

> ROSS A. HAROLD
>
> AMS MECHANICAL DESIGN LEAD ENGINEER, LMSO
>
> TRENT MARTIN
>
> AMS DEPUTY PROJ. MGR, LMSO

**Approved By:**

> KEN BOLLWEG
>
> AMS PROJECT MANAGER, LMSO
>
> J. R. BATES
>
> AMS MISSION MANAGER,
>
> PLANNING & INTEGRATION BRANCH, NASA/JSC
>
> S. S. C. TING
>
> AMS PRINCIPAL INVESTIGATOR, MIT

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# PREFACE

This Interface Control Document (ICD) represents the interface agreement
between the Alpha Magnetic Spectrometer -- 02 (AMS-02) Experiment and
the Payload Integration Hardware (PIH) for the version of the payload to
be operated on the International Space Station (ISS) for approximately
three (3) years beginning with installation on the ISS during
Utilization Flight 4 (UF4), presently designated as ISS-26-UF4 and
shuttle flight STS-130. The mission baseline is 1000 days of operational
time (24,000 hours) in full deep space view.

A precursor flight (AMS-01) was accomplished on the Space Shuttle during
the STS-91 flight and was addressed in an ICD similar to this document.
The AMS on STS-91 was operated for approximately 8.5 days during the
flight.

TABLE OF CONTENTS

[Section]{.underline} [Page]{.underline}

[**PREFACE iv**](#preface)

[ACRONYMS AND ABBREVIATIONS ix](#acronyms-and-abbreviations)

[1.0 INTRODUCTION 1](#introduction)

[1.1 GENERAL 1](#general)

[1.2 AMS PAYLOAD Description 1](#ams-payload-description)

[1.3 DOCUMENT PURPOSE 1](#document-purpose)

[2.0 DOCUMENTATION 2](#documentation)

[3.0 MANAGEMENT RESPONSIBILITIES 3](#management-responsibilities)

[3.1 JOINT RESPONSIBILITIES 3](#joint-responsibilities)

[3.1.1 Documentation 3](#documentation-1)

[3.1.2 Order of Precedence 3](#order-of-precedence)

[3.2 NASA-JSC PIB RESPONSIBILITIES 4](#nasa-jsc-pib-responsibilities)

[3.3 MIT RESPONSIBILITIES 5](#mit-responsibilities)

[4.0 MISSION OPERATIONS 6](#mission-operations)

[4.1 CARGO ELEMENT WEIGHTS 6](#cargo-element-weights)

[4.2 AMS PAYLOAD DATA INPUTS 6](#ams-payload-data-inputs)

[4.3 OPERATIONAL REQUIREMENTS AND CONSTRAINTS
6](#operational-requirements-and-constraints)

[4.3.1 Ascent 6](#ascent)

[4.3.2 On-Orbit Pre-Dock 6](#on-orbit-pre-dock)

[4.3.3 On-Orbit Dock 7](#on-orbit-dock)

[4.3.4 On-Orbit 7](#on-orbit)

[4.3.5 On-Orbit Post-Dock 7](#on-orbit-post-dock)

[4.3.6 Descent 7](#descent)

[5.0 INTERFACES 9](#interfaces)

[5.1 STRUCTURAL/MECHANICAL INTERFACES
9](#structuralmechanical-interfaces)

[5.2 CABLE INTERFACES 9](#cable-interfaces)

[5.3 SIGNAL INTERFACES 9](#signal-interfaces)

[5.4 ELECTRICAL POWER INTERFACES 9](#electrical-power-interfaces)

[5.5 FLUID INTERFACES 9](#fluid-interfaces)

[5.6 SOFTWARE INTERFACES 9](#software-interfaces)

[6.0 ENVIRONMENTAL ANALYSIS 10](#environmental-analysis)

[6.1 STRUCTURAL LOADS AND DEFLECTIONS
10](#structural-loads-and-deflections)

[6.2 THERMAL ENVIRONMENTS AND INTERFACES
11](#thermal-environments-and-interfaces)

[6.3 ELECTROMAGNETIC INTERFERENCE (EMI) ELECTROMAGNETIC COMPATABILITY
(EMC)
12](#electromagnetic-interference-emi-electromagnetic-compatability-emc)

[6.4 SHOCK, RANDOM VIBRATION, AND ACOUSTIC ENVIRONMENTS
12](#shock-random-vibration-and-acoustic-environments)

[6.5 COMMAND AND DATA, SOFTWARE, AND ELECTRICAL POWER
12](#command-and-data-software-and-electrical-power)

[6.5.1 Command and Data Management Subsystem and Software
12](#command-and-data-management-subsystem-and-software)

[6.5.2 Electrical Power 12](#electrical-power)

[6.6 MATERIALS 13](#materials)

[7.0 MISSION HARDWARE AND SOFTWARE 14](#mission-hardware-and-software)

[7.1 MISSION HARDWARE 14](#mission-hardware)

[7.1.1 PIB and MIT Provided Flight Hardware
14](#pib-and-mit-provided-flight-hardware)

[7.1.2 GSE and GHE 14](#gse-and-ghe)

[7.2 INTEGRATION SOFTWARE 14](#integration-software)

[8.0 FLIGHT OPERATIONS 19](#flight-operations)

[8.1 INTEGRATED TRAINING 19](#integrated-training)

[8.2 FLIGHT OPERATIONS CONTROL AND SUPPORT
19](#flight-operations-control-and-support)

[8.2.1 Operations Procedures 19](#operations-procedures)

[8.2.2 Flight Operations Support 19](#flight-operations-support)

[8.3 GROUND COMMAND AND CONTROL 19](#ground-command-and-control)

[8.4 MAINTENANCE PROCEDURES 20](#maintenance-procedures)

[8.5 PAYLOAD OPERATIONS WORKING GROUPS (POWG's)
20](#payload-operations-working-groups-powgs)

[8.6 OPERATIONS REVIEWS 20](#operations-reviews)

[8.7 FLIGHT PERFORMANCE EVALUATION 20](#flight-performance-evaluation)

[9.0 SAFETY 21](#safety)

[9.1 GENERAL 21](#general-1)

[9.2 DATA REQUIREMENTS 21](#data-requirements)

[10.0 INTERFACE VERIFICATION AND TESTING
23](#interface-verification-and-testing)

[11.0 SCHEDULE 24](#schedule)

[12.0 DELIVERABLES LIST 25](#deliverables-list)

[12.1 LIST OF DELIVERABLES TO BE PROVIDED BY THE PIB
25](#list-of-deliverables-to-be-provided-by-the-pib)

[12.2 LIST OF DELIVERABLES TO BE PROVIDED BY MIT
25](#list-of-deliverables-to-be-provided-by-mit)

[APPENDIX A: TO BE DETERMINED/SUPPLIED ITEMS
A-1](#appendix-a-to-be-determinedsupplied-items)

list of tables

**[Page]{.underline}**

[**TABLE 7-1 PIB PROVIDED FLIGHT HARDWARE
15**](#table-7-1-pib-provided-flight-hardware)

[**TABLE 7-2 MIT PROVIDED FLIGHT HARDWARE
16**](#table-7-2-mit-provided-flight-hardware)

[**TABLE 7-3 PIB-PROVIDED GSE AND GHE
17**](#table-7-3-pib-provided-gse-and-ghe)

[**TABLE 7-4 MIT-PROVIDED GSE AND GHE
18**](#table-7-4-mit-provided-gse-and-ghe)

# ACRONYMS AND ABBREVIATIONS

ACC Anti-coincidence Counter

ACOP AMS Crew Operations Post

AMS Alpha Magnetic Spectrometer

CCP Configuration Control Panel

CDR Critical Design Review

CIR Cargo Integration Review

CIRN European Organization for Nuclear Research

CMP Configuration Management Plan

COFR Certificate Of Flight Readiness

CR/DIR Change Request/Directive

CSR Customer Support Room

DDRS Digital Data Recording System

DOE Department Of Energy

EBCS External Berthing Cue System

ECAL Electromagnetic Calorimeter

EMC Electromagnetic Compatibility

EMI Electromagnetic Interference

EVA Extravehicular Activity

FOR Flight Operations Review

FPSR Flight Planning And Stowage Review

FRGF Flight Releasable Grapple Fixture

FRR Flight Readiness Review

GFE Government Furnished Equipment

GHE Ground Handling Equipment

GSE Ground Support Equipment

GSRP Ground Safety Review Panel

HDBK Handbook

ICD Interface Control Document

IDD Interface Design Document

ACRONYMS AND ABBREVIATIONS (Continued)

IDRD Increment Definition And Requirements Document

IPT Integrated Product Team

ISS International Space Station

ISSP International Space Station Program

JIS Joint Integrated Simulations

JISWG Joint Integrated Simulations Working Group

JOIP Joint Operations Interface Procedure

JSC Lyndon B. Johnson Space Center

KHB KSC Handbook

KSC John F. Kennedy Space Center

LEPS Low Energy Particle Shield

LMSO Lockheed Martin Space Operations

MAPTIS Materials And Processes Technology Information System

MCC Mission Control Center [OR]{.underline} Monitoring and Control
Computers

MDL Master Document List

MIL Military

MIP Mission Integration Plan

MIT Massachusetts Institute Of Technology

M/OD Meteoroid and Orbital Debris

MSFC Marshall Space Flight Center

MUA Material Usage Agreements

NASA National Aeronautics And Space Administration

NBL Neutral Buoyancy Laboratory

NHB National Aeronautics And Space Administration

Handbook

NSTS National Space Transportation System

OIU Orbiter Interface Unit

OMRS Operations And Maintenance Requirements And Specifications

ACRONYMS AND ABBREVIATIONS (Continued)

PAS Payload Attach System

PDA Payload Disconnect Assembly

PDR Preliminary Design Review

PFR Portable Foot Restraint

PIB Planning And Integration Branch

PIH Payload Integration Hardware

PMP Project Management Plan

POCC Payload Operations Control Center

POIC Payload Operations Integration Center

POWG Payload Operations Working Group

PRD Program Requirements Document

PSRP Payload Safety Review Panel

PSS Primary Support Stand

PVGF Power Video Grapple Fixture

RICH Ring Imaging Cherenkov Counter

ROEU Remotely Operated Electrical Umbilical

SRMS Shuttle Remote Manipulator System

SSP Space Station Program

SSRMS Space Station Remote Manipulator System

STA Structural Test Article

STD Standards

STE Special Test Equipment

STS Space Transportation System

TAS Tracker Assembly System

TBD To Be Determined

TCS Thermal Control System

TIM Technical Interchange Meetings

TOF Time Of Flight

TRD Transition Radiation Detector

UMA Umbilical Mechanism Assembly

USS Unique Support Structure

VAR Verification Acceptance Review

VC Vacuum Case

Vol Volume

WAD Work Authorization Document

WIF Worksite Interface

# 1.0 INTRODUCTION

## 1.1 GENERAL

In this Interface Control Document (ICD) "AMS" will refer to the total
complement of activities, hardware, software, test, integration and
operation of the Alpha Magnetic Spectrometer -- 02 (AMS-02). The flight
hardware is referred to as the "AMS Payload" and is comprised of two
parts: the "AMS Experiment" provided by the international AMS Experiment
Collaboration and the "AMS Payload Integration Hardware (PIH)" provided
by the JSC Planning and Integration Branch (PIB) of the Flight Projects
Division with the support of Lockheed Martin Space Operations (LMSO).

This ICD pertains only to the version of the AMS (AMS-02) that will be
installed and operated on the International Space Station (ISS). The
acronym "AMS-01" will be used for references to the precursor flight
version that flew on STS-91.

This ICD will be issued in two Parts. Part 1 will be the "Management"
document and Part 2 will be the "Technical" document. This is the
Management document and will be referred to herein as "this document" or
"Part 1 of this ICD."

## 1.2 AMS PAYLOAD Description 

The AMS Experiment is a state-of-the-art particle physics detector
containing a large, cryogenic superfluid helium superconducting magnet
that will be designed, constructed, tested and operated by an
international team organized under United States Department of Energy
(DOE) sponsorship. The AMS Experiment will use the unique environment of
space to advance knowledge of the universe and potentially lead to a
clearer understanding of the universe's origin. Specifically, the
science objectives of the AMS are to search for cosmic sources of
antimatter (i.e., anti-helium or heavier elements) and dark matter.

## 1.3 DOCUMENT PURPOSE

This document defines the management roles and responsibilities, the
technical activities, interfaces, list of deliverables, and schedule
requirements to accomplish the AMS Experiment to PIH integration,
launch, flight operations, post landing operations, and deintegration
activities.

# 2.0 DOCUMENTATION

The reference documents that form part of this ICD are contained in the
AMS Master Document List (MDL), JSC-29741 (LMSEAT-33971). These
documents are applicable to AMS as specified herein or in other AMS
documentation. The document revision that is in effect on the date of
approval of this ICD shall apply unless otherwise noted. A notation of
"Current issue" after date of approval indicates all future changes and
revisions are applicable to the AMS project. In the event of conflict
between this ICD and any other documents invoked herein, the contents of
this ICD shall govern.

# 3.0 MANAGEMENT RESPONSIBILITIES

The responsibility for assuring definition, control, implementation, and
accomplishment of the activities identified and agreed to in this
document is vested with the JSC PIB for all AMS Payload integration
activities and with the Massachusetts Institute of Technology (MIT) for
the AMS Experiment.

## 3.1 JOINT RESPONSIBILITIES

The PIB and MIT will provide the data products and support the necessary
analytical and physical integration activities and reviews as defined in
the master schedule in Section 11.0. The PIB and MIT will support
Technical Interchange Meetings (TIMs) with the technical personnel
responsible for the accomplishment of the integration tasks. The
interfaces and associated activities include, but are not limited to,
management, avionics, structures, thermal, flight planning, flight
operations, ground operations, and safety.

### 3.1.1 Documentation

Part 1 and Part 2 of this ICD will be jointly approved by designated
representatives of PIB and MIT. Configuration control will be initiated
upon signature approval. The PIB will maintain configuration control of
this document in accordance with JSC 27542, "Alpha Magnetic Spectrometer
(AMS) Configuration Management Plan." All proposed changes to the ICD
shall be submitted by PIB Change Request/Directive (CR/DIR) and jointly
approved by the PIB and MIT.

### 3.1.2 Order of Precedence

In the event of inconsistency between documentation, unless otherwise
expressly provided in this agreement, such inconsistency will be
resolved by giving precedence in the following order:

a.  Part 1 of this ICD

b.  Part 2 of this ICD

c.  Other Documentation

## 

## 3.2 NASA-JSC PIB RESPONSIBILITIES

The PIB is responsible for providing all AMS Payload integration
activities consisting of flight and ground safety, analytical and
physical integration, development of AMS PIH \[i.e. Unique Support
Structure -- 02 (USS-02), Cryomagnet Vacuum Case (VC), Digital Data
Recording System -- 02 (DDRS-02) etc.\], development of AMS Payload
software requirements, and AMS Payload hardware/software verification.
In addition, the PIB will provide Ground Support Equipment (GSE) and
Ground Handling Equipment (GHE) to support ground processing for the
USS-02, VC and DDRS-02.

All activities and deliverables will be performed in accordance with the
AMS-02 Master Schedule which is updated periodically by the PIB. The PIB
is responsible for identifying to MIT all integration issues that may
affect MIT responsibilities and will include a plan to resolve the
issues.

The PIB is responsible for the development of the AMS Verification Plan
which is part of the "Alpha Magnetic Spectrometer (AMS-02) Attached
Payload Hardware Interface Control Document" (SSP 57213), the AMS
Verification Data Sheet Package Closures and the Flight and Ground
Safety Data Packages. The PIB is responsible for coordinating the
development of SSP 57113, "Payload Integration Agreement for Alpha
Magnetic Spectrometer -- 02"; SSP 57113A, "Payload Integration Agreement
Increment Addendum for Alpha Magnetic Spectrometer -- 02 (AMS-02)";
SSP57213, "Alpha Magnetic Spectrometer (AMS-02) Attached Payload
Hardware Interface Control Document"; and SSP 57313, "Alpha Magnetic
Spectrometer (AMS) Software Interface Control Document" with the ISS.
The PIB is responsible for the coordinating the inclusion of AMS
requirements into the Increment Definition and Requirements Documents
(IDRDs) and IDRD Annexes for the Planning Periods involved. The PIB is
responsible for coordinating the inclusion of AMS requirements into the
Mission Integration Plan (MIPs), MIP A-level ICD and MIP Annexes for the
Shuttle flights involved. The PIB will provide AMS Payload integration
support throughout the integration/ operation/ deintegration periods.
The PIB is responsible for providing mission support activities at the
JSC Payload Operations Control Center (POCC) and AMS Payload
representation at the JSC Customer Support Room (CSR).

The PIB will convene and conduct a Preliminary Design Review (PDR) and a
Critical Design Review (CDR) for the integration activities and hardware
developed by the PIB. The PIB will support International Space Station
Program (ISSP) and Space Shuttle Program (SSP) meetings and reviews as
required to support the AMS integration process. The meetings and
reviews will include but are not limited to the following:

a.  Cargo Integration Review (CIR)

b.  Payload Flight Safety Reviews

c.  Payload Ground Safety Reviews

d.  Flight Planning and Stowage Reviews (FPSR)

e.  Verification Acceptance Review (VAR)

f.  Flight Operations Review (FOR)

g.  Flight Readiness Review (FRR)

h.  Space Shuttle Integrated Product Team (IPT) meetings

i.  Launch Package Manager's IPT meetings

## 3.3 MIT RESPONSIBILITIES

MIT is responsible for the coordination and concurrence of all the AMS
collaborators involved in the definition, design, development,
fabrication, assembly, test, checkout,

and operations of the AMS Payload. All activities and deliverables will
be performed in accordance with the AMS-02 Master Schedule which is
updated periodically by the PIB.

MIT will provide notification to the PIB whenever AMS Experiment changes
affect Part 1 and/or Part 2 of this ICD. MIT is responsible for
identifying to the PIB all AMS Experiment issues that may affect PIB
responsibilities and will include a plan to resolve the issues. Also,
MIT is responsible for the design, development, and delivery of the AMS
Experiment including Experiment GHE and GSE. MIT will provide
integration inputs and the software for the DDRS-02.

MIT is completely responsible for all issues related to the AMS Crew
Operations Post (ACOP). MIT will provide all integration, documentation,
hardware, software, training, mission operations, and planning
associated with the ACOP as this is not part of the NASA
responsibilities.

#### 

# 4.0 MISSION OPERATIONS

## 4.1 CARGO ELEMENT WEIGHTS

The PIB will publish weight and mass properties data for the AMS Payload
in appropriate ISSP and SSP documentation utilizing MIT and PIH inputs.
The PIH inputs will include items supplied by the SSP and/or ISSP and
integrated into the AMS Payload by the PIB. Control weights (and actual
weights, when available) for the AMS Experiment, USS-02, VC and other
integration hardware will be used.

## 4.2 AMS PAYLOAD DATA INPUTS

MIT will provide inputs to the PIB to allow the PIB to generate, or
support generation of, the necessary ISSP and SSP integration
documentation. The PIB will coordinate with and provide support to MIT
to complete data inputs as required.

The PIB will provide and maintain configuration control of the interface
data agreements contained in Part 1 and Part 2 of this ICD for all the
AMS interfaces.

## 4.3 OPERATIONAL REQUIREMENTS AND CONSTRAINTS

### 4.3.1 Ascent

The Super-Fluid Helium (SFHe) tank nominal vent will be opened during
the ascent phase. MIT will provide detailed requirements for the PIB
related to this vent operation. The PIB will ensure that these operation
requirements are relayed to the appropriate SSP documentation.

### 

### 4.3.2 On-Orbit Pre-Dock

The AMS Payload is to be activated on-orbit pre-dock in the Space
Shuttle for an abbreviated checkout. (This activation will not include
charging of the AMS superconducting magnet.) If the checkout is not
successful, a real time decision will be made by MIT to return the
hardware or transfer it to the ISS. Thermal conditioning of the payload
will also be performed during this period.

### 4.3.3 On-Orbit Dock 

If the pre-dock checkout is successful, the AMS Payload will be
de-activated and transferred to the ISS. The payload bay hardware will
be transferred to its assigned location on the ISS truss via the Shuttle
Remote Manipulator System (SRMS) and the Space Station Remote
Manipulator System (SSRMS). Some of the hardware stowed in the Orbiter
pressurized volume will be transferred to the ISS pressurized volume.
The AMS Payload will then be activated for operation. If anomalies are
detected prior to departure of the Space Shuttle and the Space Shuttle
timeline will allow it, a real time decision will be made by MIT to
return the hardware or leave it on the ISS.

Prior to descent, the AMS-02 external hardware will be deactivated for
transfer to the Space Shuttle. It will then be transferred to the Space
Shuttle payload bay via the SSRMS and the SRMS. The AMS-02 hardware
located in the ISS pressurized volume will also be deactivated,
transferred to the Space Shuttle and stowed for return. All hardware
will remain deactivated until transferred to the PIB representative
after landing.

### 4.3.4 On-Orbit

The AMS Payload will be operated on-orbit as specified in SSP 57113,
"Payload Integration Agreement for Alpha Magnetic Spectrometer -- 02";
SSP 57113A, "Payload Integration Agreement Increment Addendum for Alpha
Magnetic Spectrometer -- 02 (AMS-02)" and the appropriate IDRDs.

### 4.3.5 On-Orbit Post-Dock

Once the AMS is secured in the payload bay of the Space Shuttle for
return, power will be connected to the experiment via the Remotely
Operated Electrical Umbilical (ROEU) and the Auxiliary Power Control
Units (APCUs) to allow for continued monitoring of experiment systems.
Prior to deorbit prep activities, the AMS will be powered down for
return.

### 4.3.6 Descent

If the mission is aborted prior to reaching the orbit, a barometric
switch located on the AMS-02 will close the SFHe Tank nominal vent valve
during re-entry to prevent intake of air into the tank. If the mission
is aborted after reaching the orbit and if time permits, this valve will
be closed on-orbit prior to de-orbit if helium remains in the tank. In
the event of such an abort, the SFHe Tank Nominal valve should be
re-opened at TBD-1 hours post-landing to prevent rupture of the burst
valves (for mission success purposes).

###  

### 5.0 INTERFACES

The generic mechanical, electrical, avionics, thermal, and environmental
interfaces of the AMS Payload are defined in the following documents:
Part 2 of this ICD, SSP 57213, "Alpha Magnetic Spectrometer (AMS-02)
Attached Payload Hardware Interface Control Document" and the MIP
A-level ICDs. The PIB will provide the AMS Payload inputs to the ICDs
and provide subsequent review support as required. No agreements will be
made in this ICD that conflict with SSP 57213 or the MIP A-level ICDs.

## 5.1 STRUCTURAL/MECHANICAL INTERFACES

The AMS Experiment will interface with the PIB provided USS-02 and VC
utilizing the mounting locations defined in Part 2 of this ICD.

## 5.2 CABLE INTERFACES

The AMS Experiment will interface with the PIB provided cabling
utilizing the cables defined in Part 2 of this ICD.

## 5.3 SIGNAL INTERFACES

The AMS Experiment will interface with the STS provided Remotely
Operated Electrical Umbilical (ROEU)/Payload Disconnect Assembly (PDA)
and the ISS provided Umbilical Mechanism Assembly (UMA) utilizing the
data interfaces defined in Part 2 of this ICD.

## 5.4 ELECTRICAL POWER INTERFACES

The AMS Experiment will utilize the power interfaces defined in Part 2
of this ICD.

## 5.5 FLUID INTERFACES

Not applicable.

## 5.6 SOFTWARE INTERFACES

The AMS Experiment will utilize the software interfaces defined in Part
2 of this ICD.

# 6.0 ENVIRONMENTAL ANALYSIS

Environmental analysis will be conducted to determine physical and
functional interface compatibility of the AMS Payload. The specific
analyses and responsibilities are described in the following sections.
MIT will provide analytical inputs to the PIB to support these analyses.

The natural and induced environments are defined in SSP 57213 and the
MIP A-level ICD.

All design, certification and integration activities will be
accomplished in accordance with the AMS-02 Master Schedule which is
updated periodically by the PIB.

A list of hardware and documentation deliverables is contained in
Section 12.0.

## 6.1 STRUCTURAL LOADS AND DEFLECTIONS

The design requirements found in SSP 57213 and the MIP A-level ICD
correspond to the ISS, Shuttle and USS-02 loading environments and are
recommended as minimum conditions to which MIT should develop their
preliminary design. Subsequent design will be based upon coupled dynamic
and quasi-static analyses performed using updated AMS Experiment,
USS-02, Shuttle and ISS models. MIT is responsible for assuring that the
experiment is designed to be compatible with the ISS, Shuttle and USS-02
environments resulting from these analyses and any subsequent updates.
The PIB is responsible for assuring that the interface forces and
deflections (including thermal effects and manufacturing tolerances) do
not exceed the limits specified in SSP 57213, the MIP A-level ICD and
this ICD, based on analysis of the integrated system.

The PIB will provide an approach for AMS Payload strength verification
and mathematical verification, and obtain MIT's concurrence. These
written plans for strength verification and mathematical model
verification will be provided to the Payload Safety Review Panel (PSRP).
Any AMS Payload deviation in the approach from ISSP and SSP requirements
must be documented before the fact as a deviation with which the PIB has
concurred. The results of structural verification testing by MIT as
required by the JSC ISSP and SSP will be provided to the PIB.

The results of the ISS verification loads cycle and the SSP verification
loads analysis will be used by the PIB to ensure that the interface
loads and relative deflections are within the ISS, Orbiter and AMS
Payload capability. The PIB and MIT are responsible for verifying the
AMS Payload compatibility with these loads, and for verifying that the
dynamic envelope (including thermal effects and manufacturing
tolerances) does not exceed the allowable limits, as specified in SSP
57213 and the MIP A-level ICDs, based on the integrated system analyses.

Refer to the latest revision of JSC 28792, "Alpha Magnetic Spectrometer
-- 02 Structural Verification Plan for the Space Transportation System
and the International Space Station " for definition and products
associated with the structural verification process.

The PIB developed models, analyses, and reports will conform to NSTS
32329, "Structural Integration Analyses Responsibility Definition for
Space Shuttle Vehicle and Cargo Element Developers."

## 6.2 THERMAL ENVIRONMENTS AND INTERFACES 

The generic thermal design parameters used for integrated thermal
analyses of the AMS Payload are provided in SSP 57213 and the MIP
A-level ICDs. The mission unique requirements are defined in Part 2 of
this ICD. The PIB is responsible for assuring that the AMS Payload is
designed to be compatible with the ISS and Orbiter environments as
specified in Part 2 of this ICD.

MIT will provide the most recent versions of the AMS thermal models to
the PIB. The PIB will develop an integrated AMS Payload/Orbiter model
and an integrated AMS Payload/ISS model and will perform the required
integrated thermal analyses. The AMS Payload thermal reports containing
the results of these analyses will be provided in the appropriate design
review data package.

The PIB will provide preflight thermal predictions to MIT to be used for
experiment and real time mission support. These analyses will utilize
MIT provided mission timelines for power requirements and ISS attitudes.

## 6.3 ELECTROMAGNETIC INTERFERENCE (EMI) ELECTROMAGNETIC COMPATABILITY (EMC)

The PIB is responsible for assuring that the AMS Payload interfaces meet
the induced electromagnetic Interference environment, and that the
entire AMS Payload complies with the conductive and radiated emission
requirements defined in SSP 57213, the MIP ICDs and part 2 of this ICD.
The specific characteristics of the emission sources, if any, will be
provided by the PIB. The PIB is responsible for assuring compliance with
the design requirements for electrical bonding, circuit return isolation
and grounding, and wire separation at the interface and within the AMS
Payload where it affects the interface. MIT retains the responsibility
for assuring that the AMS Experiment operates properly in the
electromagnetic environment specified in Part 2 of this ICD.

## 6.4 SHOCK, RANDOM VIBRATION, AND ACOUSTIC ENVIRONMENTS 

The PIB is responsible for verifying the compatibility of the AMS
Payload with the Shuttle induced shock, random vibration, and acoustic
environments defined in the MIP A-level ICD and Part 2 of this ICD. It
is also responsible for verifying the compatibility at the AMS Payload
with the ISS shock, random vibration and microgravity environments
defined in SSP 57213.

## 6.5 COMMAND AND DATA, SOFTWARE, AND ELECTRICAL POWER 

### 6.5.1 Command and Data Management Subsystem and Software

The PIB is responsible for assuring that the AMS Payload is designed to
be compatible with the capabilities and constraints of the Shuttle and
ISS data systems. Design requirements and guidelines for the payload are
provided in Part 2 of this ICD. MIT will provide to the PIB sufficient
information to allow the generation of MIP Annex 4 for command and data
during the checkout of the AMS Payload while in the Orbiter and to
coordinate the development of AMS Payload command and data requirements
in ISS documentation while installed on the ISS.

### 6.5.2 Electrical Power

The PIB is responsible for assuring that the payload is designed to be
compatible with the capabilities and constraints of the Space Station
and Space Shuttle power systems. Design requirements and guidelines for
the payload are provided in Part 2 of this ICD. The PIB will perform a
payload compatibility analysis for the power system. This analysis will
include power, voltage drop, circuit breaker, and fuse compatibility

between the payload requirements and the Space Station/Shuttle
capability and constraints. The data, results, and updates will be
provided to MIT in support of the flight readiness reviews.

## 6.6 MATERIALS

Materials and processes for integration hardware manufactured at JSC
shall meet

SE-M-0096, "General Specification for Materials and Processes
Requirements for JSC controlled Payloads," and the materials
requirements of sections 208.3 and 209 of NSTS 1700.7B and NSTS 1700.7B
ISS Addendum. Evaluation of materials for outgassing, flammability,
corrosion, and stress corrosion cracking can be obtained from
MSFC-HDBK-527/JSC-09604, "JSC GFE Materials Selection List and Materials
Documentation Procedures," and the Materials and Processes Technology
Information System (MAPTIS) internet web site.

# 7.0 MISSION HARDWARE AND SOFTWARE

## 7.1 MISSION HARDWARE

### 7.1.1 PIB and MIT Provided Flight Hardware

The PIB and MIT provided flight hardware is identified in Table 7-1 and
Table 7-2, respectively. The configuration and interface definition of
the flight hardware supplied by the PIB is defined in Part 2 of this
ICD.

MIT will identify to the PIB the location of subsystem temperature
sensors on the payload equipment mounted on the USS-02, by joint
agreement, and as defined in

Part 2 of this ICD.

### 7.1.2 GSE and GHE

Table 7-3 and Table 7-4 identify the PIB and MIT provided GSE and GHE,
respectively, that is required to support AMS Payload ground processing
and testing.

## 7.2 INTEGRATION SOFTWARE

MIT will provide a subsystem instrumentation and command list to the
PIB, which will contain display and control parameters relative to AMS
Payload subsystems. The PIB will utilize this list in the development of
command and data requirements in MIP Annex 4, SSP 57113 and SSP 57313.

######### TABLE 7-1 PIB PROVIDED FLIGHT HARDWARE

+-----------------------------------------------------+----------------+
| **ITEMS**                                           | **UNITS**      |
+-----------------------------------------------------+----------------+
| \* External Berthing Cue System (EBCS), and cables  | 1              |
| and brackets                                        |                |
+-----------------------------------------------------+----------------+
| \* EVA (Extravehicular Activity) handrails/ Tether  | 10 or less     |
| attach points                                       |                |
+-----------------------------------------------------+----------------+
| \* Flight Releasable Grapple Fixture (FRGF), and    | 1              |
| cables and brackets                                 |                |
+-----------------------------------------------------+----------------+
| \* Portable Foot Restraints (PFR) Worksite          | 2 or less      |
| Interface (WIF)                                     |                |
+-----------------------------------------------------+----------------+
| \* Power Video Grapple Fixture (PVGF), and cables   | 1              |
| and brackets                                        |                |
+-----------------------------------------------------+----------------+
| \* ROEU/PDA, and cables and brackets                | 1              |
+-----------------------------------------------------+----------------+
| \* Umbilical Mechanism Assembly (UMA) (Passive      | 1              |
| Half), and cables and brackets                      |                |
+-----------------------------------------------------+----------------+
| Cryomagnet Vacuum Case (VC) (Flight Article)        | 1              |
+-----------------------------------------------------+----------------+
| Power Distribution Box (PDB)                        | 1              |
+-----------------------------------------------------+----------------+
| Meteoroid and Orbital Debris (M/OD) shields         | 2              |
+-----------------------------------------------------+----------------+
| Payload Attach System (PAS) (Passive Half)          | 1              |
+-----------------------------------------------------+----------------+
| EVA Interface Panel (Interface to UMA)              | 1              |
+-----------------------------------------------------+----------------+
| Interface Panel A (Interface to ROEU)               | 1              |
+-----------------------------------------------------+----------------+
| Cabling from interface panels to J-Crate and PDB    | --             |
+-----------------------------------------------------+----------------+
| DDRS --02 and associated cabling/interface cards    | 1              |
+-----------------------------------------------------+----------------+
| Trunnion scuff plates for deployable payload        | 4              |
|                                                     |                |
|                                                     | (Part of       |
|                                                     | USS-02)        |
+-----------------------------------------------------+----------------+
| Thermal Blankets                                    | TBD-2          |
+-----------------------------------------------------+----------------+
| Unique Support Structure-02 (USS-02)                | 1              |
+-----------------------------------------------------+----------------+
| Monitoring and Control Computers (MCC)              | 2              |
+-----------------------------------------------------+----------------+

\* Items supplied by NASA STS or ISS and integrated into AMS Payload by
the JSC PIB.

######### TABLE 7-2 MIT PROVIDED FLIGHT HARDWARE

  ------------------------------------------------------ ----------------
  **ITEMS**                                              **UNITS**

  Transition Radiation Detector (TRD)                    1

  TRD Gas System                                         1

  Upper and Lower Time-Of-Flight (TOF) Scintillator      1 each
  Assembly                                               

  AMS-02 Silicon Tracker Assembly                        1

  Tracker Alignment System (TAS)                         1

  Anti-Coincidence Counter (ACC)                         1

  Ring Imaging Cherenkov Counter (RICH)                  1

  Electromagnetic Calorimeter (ECAL)                     1

  Thermal Control System (TCS)                           1

  AMS Crew Operations Post (ACOP)                        1

  Experiment Avionics including Star Tracker             1
  ------------------------------------------------------ ----------------

######### TABLE 7-3 PIB-PROVIDED GSE AND GHE

  ------------------------------------------------------ ----------------
  **ITEMS**                                              **UNITS**

  VC Structural Test Article (STA)                       1

  Primary Support Stand (PSS)                            1

  Lower USS Support Fixture                              1

  Primary Lifting Fixture                                1

  Multi-purpose Lifting Fixture                          1

  Intermediate Support Fixtures                          4

  USS-02 Assembly Fixture                                1

  Special Test Equipment (STE) for structural testing    Multiple

  \* Neutral Buoyancy Laboratory (NBL) mockups           2

  VC/Magnet Shipping Fixture                             2
  ------------------------------------------------------ ----------------

######### TABLE 7-4 MIT-PROVIDED GSE AND GHE

  ------------------------------------------------------ ----------------
  **ITEMS**                                              **UNITS**

  Cryomagnet GSE                                         N/A

  TRD GSE                                                N/A

  TCS GSE                                                N/A

  TCS STAs                                               TBD-3

  GSE Dewar Lifting Sling                                TBD-4

  Experiment Electrical GSE                              N/A

  STA Cold Mass Replica                                  1

  STA He Tank                                            1

  STA Cryo System                                        1

  Possible Magnet Operation Alert System                 1

  Possible Metal Detector                                1

  GSE Batteries                                          TBD-5

  Shipping Containers                                    TBD-6
  ------------------------------------------------------ ----------------

# 8.0 FLIGHT OPERATIONS

## 8.1 INTEGRATED TRAINING

MIT and PIB will support the Joint Integrated Simulations (JIS's)
conducted by the SSP. MIT and PIB will also support the associated Joint
Integrated Simulations Working Groups (JISWG's).

## 8.2 FLIGHT OPERATIONS CONTROL AND SUPPORT

### 8.2.1 Operations Procedures

The PIB and MIT will assist the SSP in the development of the Joint
Operations Interface Procedures (JOIP's) for the Space Shuttle flights
and will assist the ISS in the development of the operational procedures
for the on-orbit operation on the ISS.

### 8.2.2 Flight Operations Support

The PIB will make provisions for MIT's representative(s) in the JSC
Mission Control Center (MCC) CSR during the Space Shuttle flights that
transport the AMS Payload. The PIB will provide representatives at the
CSR during these flights to provide a contact for assessment of the
in-flight performance of the AMS Payload.

AMS personnel will utilize the JSC POCC to support on-orbit AMS Payload
checkout in the Orbiter, and installation and checkout on the ISS.

## 8.3 GROUND COMMAND AND CONTROL

After installation on the ISS and transition from the JSC POCC, ground
command and control of the AMS Payload will originate from the MIT/CERN
remote Payload Operations Control Center and will be routed through the
Payload Operations Integration Center (POIC) at Marshall Space Flight
Center (MSFC). The PIB will make provisions for the use of the POIC.

## 8.4 MAINTENANCE PROCEDURES

There is no planned maintenance for the AMS-02 external hardware.
However, the PIB, MIT, and the STS/ISS representatives will jointly
develop and agree on a maintenance procedure, should a real time
situation requires one.

MIT shall provide maintenance procedures for ACOP, and the PIB shall
develop maintenance procedures for DDRS-02. MIT will support PIB for
inclusion of these procedures in the appropriate IDRD Annex 2.

## 8.5 PAYLOAD OPERATIONS WORKING GROUPS (POWG's)

MIT will support the PIB in Payload Operations Working Group (POWG)
meetings conducted by the SSP to develop and refine operational
scenarios and to resolve operational issues as the basis of flight
rules, plans, and procedures addressing nominal and off-nominal
situations.

## 8.6 OPERATIONS REVIEWS

MIT will assist the PIB to support the Station/Space Shuttle during
reviews of flight rules, plans, and procedures for implementation of,
and/or compatibility with, carrier and payload operations, requirements,
and constraints.

## 8.7 FLIGHT PERFORMANCE EVALUATION

The PIB will perform a post-flight mission evaluation, and prepare
integrated payload mission evaluation report of the AMS Payload.

# 9.0 SAFETY

## 9.1 GENERAL

The PIB is responsible for assuring the PSRP and the Ground Safety
Review Panel (GSRP) that the AMS Payload and its GSE, including
interfaces and operations, are safe. MIT shall provide any and all
safety related input to the PIB for inclusion in the safety packages and
support the safety reviews, as required. The AMS Payload and GSE design
and operations must comply with the safety requirements defined in NSTS
1700.7B, NSTS 1700.7B ISS Addendum, 45 SW HB S-100/KHB 1700.7, and Part
2 of this ICD. Payload compliance with the Space Shuttle and Space
Station safety requirements is assessed by the PIB through the SSP
flight and ground safety reviews.

The PIB will provide hazard analyses of the AMS Payload, GHE, and GSE to
support the payload safety reviews. The PIB will assess changes to the
AMS Payload hardware affecting flight and ground safety against NSTS
1700.7B, NSTS 1700.7B ISS Addendum and 45 SW HB S-100/KHB 1700.7. These
assessments will be presented to the PSRP and GSRP, as appropriate.

Any updates to the AMS Payload design since the last presentation to the
safety review panels will be presented to the panels at the next AMS
Payload safety review. This will include new waivers and Material Usage
Agreements (MUA's), applicable revised hazards, significant safety
problems and anomalies. In conjunction with the Space Shuttle FOR, the
integration hardware including systems and procedures, will be reviewed
to highlight any safety concerns.

The PIB will prepare and submit a Certificate of Flight Readiness (COFR)
for the AMS Payload to the ISSP and SSP.

## 9.2 DATA REQUIREMENTS

The PIB will submit to MIT a copy of all AMS Payload flight and ground
safety review data packages required by the SSP.

To insure safety compatibility of the AMS Payload, the PIB-provided
hazard analysis reports will identify potential failure/fault conditions
associated with payload design or operations, or payload utilization of
Orbiter and Space Station services, that propagate across the interface
to create a hazardous condition. Such conditions will include functional
failure (loss of power, command, signal processing, thermal control,
etc.) that could cause a payload hazard, failures of Space Station
and/or Orbiter safety accommodations (caution and warning, safing, fire
detection and suppression, etc.), and payload failures that could exceed
the design criteria in Part 2 of this ICD. Assumptions made by the PIB
with respect to Orbiter and/or Space Station services and operations
associated with hazardous payload functions will be defined in the
flight and ground safety data packages in accordance with NSTS 1700.7B,
NSTS 1700.7B ISS Addendum and 45 SW HB S-100/KHB 1700.7.

The PIB and MIT will jointly identify in Part 2 of this ICD all power
and signals (commands and monitoring) used for control of safety
critical functions. For this input, payload safety critical functions
are those electrical functions that must comply with the failure
tolerance requirements of NSTS 1700.7B and NSTS 1700.7B ISS Addendum.
Where subsystem equipment and/or wiring is involved in meeting the
failure tolerance requirement, PIB will define such planned usage.
Safety critical services required by the payload, in the areas of fault
detection or emergency safing commands, must be obtained directly from
SSP and the ISSP.

# 10.0 INTERFACE VERIFICATION AND TESTING

The PIB is responsible for the confirmation that all AMS Payload
interface and safety requirements have been met. A combination of test,
analyses, and inspections will be performed at the AMS Payload level to
verify that the as-built hardware is in

accordance with design requirements and/or constraints prior to delivery
to the SSP. The PIB will perform analyses prior to physical integration
of the AMS Experiment to verify that the total payload does not violate
Shuttle and ISS interfaces, resources, and constraints.

MIT will provide the AMS Experiment assembly drawing numbers to the PIB
for call up in the top payload installation/assembly drawing, making the
AMS Payload drawing represent the entire cargo element. The PIB and MIT
will prepare an AMS Payload assembly drawing to document the mission
configuration. The PIB will provide updates to the assembly drawing as
required to document the as-built configuration of the AMS Payload. MIT
will provide certification to the PIB that the models provided to the
PIB for USS-02 verification analyses (reference Section 6.1) represent
the as-built, as-integrated AMS Experiment hardware installed on the
USS-02 and VC.

AMS Payload-to-Space Shuttle (Level I) interface verification
requirements to be accomplished at the launch site will be submitted by
the PIB in the Operations and Maintenance Requirements and
Specifications (OMRS) File II. Vol. II. This will include identifying
safety critical requirements that require PIB approval of implementing
KSC Work Authorization Documents (WAD's).

The PIB is responsible for verifying compatibility of AMS Payload
interfaces as defined in Part 2 of this ICD. MIT will provide interface
verification requirements to the PIB so that the PIB can generate MIP
Annex 9, "Payload Verification Requirements." For any interfaces that
cannot be verified, MIT will provide supporting rationale for
non-verification.

MIT's input to MIP Annex 9 will also cover servicing and maintenance
requirements. This will include identifying any safety critical
requirements that require PIB approval of implementing KSC WAD's.

# 11.0 SCHEDULE

All activities and deliverables will be performed in accordance with the
AMS-02 Master Schedule which will be updated periodically by the PIB. It
will include schedule of design, certification, and integration for the
AMS Payload. Dates indicated on the schedule will be directly related to
the launch date of the AMS-02 flight. Due to the dynamic nature of the
Space Shuttle and ISS manifest, the AMS-02 Master Schedule will be
adjusted periodically per the current Space Shuttle and ISS manifest.
Necessary changes to the planned dates will be coordinated between the
PIB and MIT, but will not require formal Configuration Control Panel
(CCP) approval.

# 12.0 DELIVERABLES LIST

## 12.1 LIST OF DELIVERABLES TO BE PROVIDED BY THE PIB

-   Master Schedule

-   KSC integration schedule

-   Structural verification (modal and static test) schedule

-   Flight hardware as listed in Table 7-1

-   GSE and GHE as listed in Table 7-3

-   Integration schematic for the circuitry grounding and shield
    grounding

-   Verification Plan for the AMS Payload

-   Flight Safety Data Packages

-   Ground Safety Data Packages

-   ICD for AMS Experiment interfaces to PIH

-   A PDR data package

-   A CDR data package

-   Program Requirements Document/Project Management Plan (PRD/PMP)

-   Mechanical drawings/schematics for the flight and ground equipment

-   Electrical drawings/schematics for the flight and ground equipment

-   Thermal Analysis Reports

-   Structural Verification Plan for the AMS Payload

-   Configuration Management Plan (CMP) for the AMS project

-   Project Master List of Documents and Specifications for the AMS
    project

-   Functional test procedures

-   Mass Budget and Mass Properties Reports

-   Top Assembly Drawing and Drawing Tree

## 12.2 LIST OF DELIVERABLES TO BE PROVIDED BY MIT

-   Static bonding strap locations

-   Integration schematics for AMS Experiment interface circuitry
    grounding and shield grounding

-   Thermal requirements and thermal control system design

-   AMS Experiment shipping container (only if necessary to ship AMS
    Experiment independent of the USS-02 and its related shipping
    containers)

-   AMS Experiment and final assembly drawing

-   Flight hardware as listed in Table 7-2

-   GSE and GHE as listed in Table 7-4

-   AMS bus monitor software

-   AMS bus monitor card

-   Structural analysis and test data for the secondary structure

-   Materials list and data

#### 

# APPENDIX A: TO BE DETERMINED/SUPPLIED ITEMS

TBD-1 Subject: Number of hours post-landing the SFHe Tank Nominal Valve
should be re-opened.

TBD-2 Subject: Quantity of PIB supplied thermal blankets (Table 7-1)

TBD-3 Subject: Quantity of MIT supplied TCS STAs (Table 7-4)

TBD-4 Subject: Quantity of MIT supplied GSE Dewar Lifting Sling (Table
7-4)

TBD-5 Subject: Quantity of MIT supplied GSE Batteries (Table 7-4)

TBD-6 Subject: Quantity of MIT supplied Shipping Containers (Table 7-4)