50104a.pdf

SSP 50104, Revision A

National Aeronautics and Space Administration International Space Station Program Johnson Space Center Houston, Texas Contract No. NAS15–10000

International Space Station Program

November 1996

Portable Breathing Apparatus Standard Interface Control Document

SSP 50104, Revision A November 1996

REVISION AND HISTORY PAGE

REV. DESCRIPTION PUB.

DATE

– Initial Release 08–01–95

A Revision A per SSCD 000519, EFF. 03–04–97 03–31–97 Incorporate PIRNs 50104–NA–0001, 50104–NA–0002A, 50104–NA–0003A, 50104–NA–0004, 50104–NA–0005, 50104–NA–0006, 50104–NA–0007C, 50104–NA–0008, 50104–NA–0009, 50104–NA–0010, 50104–NA–0011, 50104–NA–0012, 50104–NA–0013, 50104–NA–0014A, 50104–NA–0015C, 50104–NA–0017, 50104–NA–0018, 50104–NA–0019, 50104–NA–0020, 50104–NA–0021, 50104–NA–0022A, 50104–NA–0023.

i

INTERNATIONAL SPACE STATION PROGRAM

PORTABLE BREATHING APPARATUS STANDARD

INTERFACE CONTROL DOCUMENT

NOVEMBER 1996

CONCURRENCE

Prepared By:

Approved By:

Signature /s/

ISS Program

Approved By:

Product Group 1

Prime ICWG: Howard S. Griffin

Darren L. Riggle/ LESC Deborah S. Bourland/ SP4

Signature /s/

James L. Lewis, PhD./ SP

Signature /s/

Signature /s/

James W. McBarron, II/ EC

(NASA)

Subsystem Approval By:

Signature /s/

Bruce W. Sauser/ EC5Subsystem Approval By:

Signature /s/

William R. Jones

Signature /s/

ISS Program (Boeing)

Arthur L. Scheuermann

Signature /s/

Product Group 3

Signature /s/

Signature /s/

Darren L Riggle 4–27–95 Deborah S Bourland 4–24–95

Bruce W. Sauser 4–25–95

Arthur L. Scheuermann 4–27–95

James L. Lewis 27Apr95

James W. McBarron, II

William R. Jones 4–27–95

Larry Ballentine 5/15/95L. T. Archibald 6/6/95

DQA:

Signature /s/

Jeff Prince

Jeff Prince 06/27/95Jeff Prince i

PREFACE

The contents of this document are intended to be consistent with the tasks and products to be prepared by Program participants. The Portable Breathing Apparatus Standard Interface Control Document shall be implemented on all new International Space Station ISS contractual and internal activities and shall be included in any existing contracts through contract changes. This document is under the control of the Space Station Control Board, and any changes or revisions will be jointly agreed upon and signed by NASA, International Space Station Program Office (NASA and Boeing), Product Group –1, and Product Group –3.

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TABLE OF CONTENTS

PARAGRAPH PAGE

1.0 INTRODUCTION 1 - 1

1.1 PURPOSE 1 - 1

1.2 ORDER OF PRECEDENCE 1 - 1

1.3 PROTOCOL 1 - 1

2.0 DOCUMENTS 2 - 2

2.1 APPLICABLE DOCUMENTS 2 - 2

2.1.1 GOVERNMENT DOCUMENTS 2 - 2

2.1.1.1 MILITARY 2 - 2

2.1.1.1 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION 2 - 2

2.1.1.3 DRAWINGS 2 - 3

3.0 INTERFACE DESCRIPTION 3 - 1

3.1 PORTABLE BREATHING APPARATUS 3 - 1

3.1.1 GENERAL 3 - 1

3.1.1.1 ITEM DESCRIPTION 3 - 1

3.1.1.2 INTERFACE DESCRIPTION 3 - 3

3.1.1.2.1 MAN–MACHINE INTERFACE: ON–ORBIT STOWAGE MODE 3 - 3

3.1.1.2.2 MAN–MACHINE INTERFACE: OPERATING MODE 3 - 5

3.1.1.2.3 LAUNCH STOWAGE MODE 3 - 5

3.1.1.3 INTERFACE RESPONSIBILITIES 3 - 5

3.1.1.3.1 OXYGEN ACCESS PORT 3 - 5

3.1.1.3.2 BRACKET INSTALLATION 3 - 5

3.1.1.3.3 EQUIPMENT MOUNTS 3 - 5

3.1.1.3.4 FASTENERS 3 - 6

3.1.1.4 COORDINATE SYSTEM 3 - 6

3.1.1.5 ENGINEERING UNITS, TOLERANCES, AND CONVERSIONS 3 - 6

3.1.2 INTERFACE REQUIREMENTS 3 - 6

3.1.2.1 INTERFACE PLANE 3 - 6

3.1.2.1.1 ENVELOPE INTERFACES 3 - 6

3.1.2.1.2 VOLUME CONFIGURATION 3 - 11

3.1.2.2 MASS PROPERTIES 3 - 11

3.1.2.3 STRUCTURAL INTERFACES 3 - 12

3.1.2.3.1 STRUCTURAL LOADS 3 - 12

3.1.2.3.2 CENTER OF GRAVITY 3 - 12

3.1.2.4 MECHANICAL INTERFACES 3 - 15

3.1.2.4.1 INSTALLATION FASTENERS 3 - 15

3.1.2.4.2 SUPPORTING STRUCTURE AND BRACKETS 3 - 15

3.1.2.4.3 ELECTRICAL 3 - 15

3.1.2.4.4 CLAMPING 3 - 15

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TABLE OF CONTENTS

PARAGRAPH PAGE

3.1.2.4.5 ADHESIVE 3 - 15

3.1.2.4.6 EQUIPMENT RESTRAINT DURING LAUNCH 3 - 16

3.1.2.5 FLUID INTERFACES 3 - 16

3.1.2.6 ELECTRICAL INTERFACES 3 - 17

3.1.2.6.1 ELECTRICAL / COMMUNICATION INTERCONNECT 3 - 17

3.1.2.6.2 CONNECTOR PIN ASSIGNMENTS 3 - 19

3.1.2.6.3 INTERCONNECT DIAGRAM 3 - 19

3.1.2.6.4 ELECTRICAL CONNECTOR SPECIFICATIONS 3 - 20

3.1.2.7 ENVIRONMENTS 3 - 20

3.1.2.7.1 THERMAL 3 - 20

3.1.2.7.1.1 NON–OPERATING 3 - 20

3.1.2.7.1.2 ON–ORBIT OPERATING 3 - 20

3.1.2.7.1.3 AMBIENT COOLING 3 - 20

3.1.2.7.2 PRESSURE 3 - 20

3.1.2.7.2.1 OPERATING 3 - 20

3.1.2.7.2.2 NON–OPERATING 3 - 20

3.1.2.7.2.3 DE–PRESSURIZATION / RE–PRESSURIZATION 3 - 21

3.1.2.7.3 AMBIENT HUMIDITY 3 - 21

3.1.2.7.3.1 ON–OPERATING 3 - 21

3.1.2.7.3.2 ON–ORBIT OPERATING 3 - 21

3.1.2.7.4 ACCELERATION 3 - 21

3.1.2.7.4.1 NON–OPERATING 3 - 21

3.1.2.7.4.2 ON–ORBIT OPERATING 3 - 22

3.1.2.7.5 VIBRATION 3 - 22

3.1.2.7.5.1 NON–OPERATING 3 - 22

3.1.2.7.5.2 ON–ORBIT OPERATING 3 - 22

3.1.2.7.6 ELECTROMAGNETIC EFFECTS 3 - 22

3.1.2.7.6.1 ELECTROMAGNETIC COMPATIBILITY 3 - 22

3.1.2.7.6.2 ELECTROMAGNETIC INTERFERENCE 3 - 22

3.1.2.7.6.3 BONDING 3 - 22

3.1.2.7.7 ACOUSTIC 3 - 23

APPENDIX A

ABBREVIATIONS AND ACRONYMS A - 1

APPENDIX B

DETAILED DRAWINGS B - 1

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LIST OF FIGURES

FIGURE PAGE

3.1.1.1–1 CYLINDER RETAINING BRACKET/CLIP, LAUNCH STOWAGE MODE 3 - 2

3.1.1.1–2 CYLINDER RETAINING BRACKET/CLIP, ON–ORBIT STOWAGE MODE 3 - 2

3.1.1.2.1–1 MASK HOLDER/MASK ASSEMBLY, ACCESS AREA 3 - 3

3.1.1.2.1–2 REDUCER/CYLINDER MOUNTED ASSEMBLY ACCESS AREA 3 - 4

3.1.2.1–1 PBA TO ISS INTERFACE PLANE (STOWAGE AND OPERATING) 3 - 7

3.1.2.1.1–1 PBA HARDWARE INTERFACE FOOTPRINTS AND HOLE PATTERNS 3 - 8

3.1.2.1.1–2 CYLINDER/MOUNT BRACKET ENVELOPE 3 - 9

3.1.2.1.1–3 MASK HOLDER/MASK ENVELOPE 3 - 10

3.1.2.1.1–4 EXTENSION HOSE/TEE KIT ENVELOPE 3 - 11

3.1.2.3.2–1 CYLINDER/MOUNT CENTER OF GRAVITY (CG) 3 - 13

3.1.2.3.2–2 MASK HOLDER/MASK CENTER OF GRAVITY (CG) 3 - 14

3.1.2.3.2–3 EXTENSION HOSE/TEE KIT CENTER OF GRAVITY (CG) 3 - 14

3.1.2.6.1–1 PBA COMMUNICATION INTERFACE 3 - 17

3.1.2.5–1 QUICK DISCONNECT ASSEMBLY 3 - 18

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LIST OF TABLES

TABLE PAGE

3.1.2.2–1 MASS PROPERTIES OF THE PBA COMPONENTS 3 –12

3.1.2.3.2–1 CENTER OF GRAVITY OF PBA ASSEMBLIES 3 –12

3.1.2.6.2–1 INTERFACE CHARACTERISTICS BETWEEN PBA AND HCU 3 –19

3.1.2.7.4–1 SECONDARY STRUCTURE STEADY STATE ACCELERATION 3 –21

3.1.2.7.5–1 RANDOM VIBRATION ENVIRONMENTS FOR EQUIPMENT DESIGN 3 –22

3.1.2.7.7–1 ISS ELEMENT INTERNAL ACOUSTIC SPECTRUM 3 –23

1 - 1

1.0 INTRODUCTION

1.1 PURPOSE

The purpose of this document is to define the hardware interfaces and interface performance characteristics between the Portable Breathing Apparatus (PBA) hardware assembly and the ISS and its partners. This document is the sole source for detailed interface agreement between the preparer, NASA, and the affected partners responsible for habitable enclosure’s packaging configuration.

This document encompasses all dedicated interfaces between the PBA and the ISS manned elements. Hard–lined interface with station oxygen and audio communication systems will be controlled by this document.

1.2 ORDER OF PRECEDENCE

In the event of conflict between SSP 41000, System Specification for the International Space Station Alpha, and the contents of this Interface Control Document (ICD), the requirements of SSP 41000 shall take precedence.

1.3 PROTOCOL

Deleted

2 - 2

2.0 DOCUMENTS

2.1 APPLICABLE DOCUMENTS

The following documents of the date and issue shown include specifications, models, standards, guidelines, handbooks, and other special publications. The status of documents identified may be determined from the International Space Station Program Baseline Activity Index and Status Report.

2.1.1 GOVERNMENT DOCUMENTS

2.1.1.1 MILITARY

MIL–STD–130G Identification Marking of U.S. Military Property

MIL–STD–5087B Bonding, Electrical, and Lighting Protection for Aerospace Systems

2.1.1.1 NATIONAL AERONAUTICS AND SPACE ADMINISTRATION

SSP 50005B Flight Crew Systems Integration Standards for the International Space Station

SSP 50006 Internal and External Decal and Placards Specification

SSP 50007 Space Station Inventory Management System Label Specification

NASA–TM–86538 Design and Verification Guidelines for Vibroacoustic and Transient Environments

SS–CM–465–A009 Critical Item Development Specification for Space Station Program Crew Headset Assembly and Cascading Cable

SSP 30219D Space Station Reference Coordinate System

SSP 30237B Space Station Electromagnetic Emission and Susceptibility Requirements for Electromagnetic Compatibility

SSP 30238B Space Station Electromagnetic Techniques

SSP 30243C Space Station System Requirements for Electromagnetic Compatibility

SSP 30245B Space Station Electrical Bonding Requirements

SSP 30423E Space Station Approved Electrical, Electronic, and Electromechanical Parts List

2 - 3

SSP 30459E Space Station Interface Development Process Requirements

JSC 27058 End Item Specification for the International Space Station Alpha Portable Breathing Apparatus

SSP 30260:19 Audio Terminal Unit Interface Control Document

SSQ 25002B Supplemental List of Qualified Electrical, Electronic, and Electromechanical (EEE) Parts, Manufactures, and Laboratories (QEPM&L)

2.1.1.3 DRAWINGS

2000 166–105 Lemo connector plug

2000 166–104 Lemo female receptacle

3 - 1

3.0 INTERFACE DESCRIPTION

3.1 PORTABLE BREATHING APPARATUS

3.1.1 GENERAL

3.1.1.1 ITEM DESCRIPTION

The Portable Breathing Apparatus (PBA) is a Government Furnished Equipment (GFE) element in the Portable Emergency Provisions (PEP) subsystem that will be launched and stowed within designated close–out lockers. The interface requirements stated in this document are applicable when designing for the mechanical, electrical, fluid (oxygen) and human interactions of the PBA and the International Space Station (ISS) structures. The application of these requirements will allow the crew to access the emergency equipment most effectively.

This document defines the physical interfaces of the PBA hardware to the Space Station modules. These include one stowage configuration and one operating configuration. The PBA hardware and locker will have one unique interface requirement. The functional requirements will be configuration dependent.

The launch stowage configuration will accommodate all of the PBA hardware that is physically mounted and held securely in place. Figure 3.1.1.1–1, Cylinder Retaining Bracket/Clip, Launch Stowage Mode shows the launch stowage mode. The on–orbit stowage configuration will allow quick access to the PBA mask and cylinder assembly. This is shown in Figure 3.1.1.1–2, Cyliner Retaining Bracket/Clip On–Orbit Stowage Mode.

The operating configuration requires communication connector interface, which will be discussed in the electrical interface section of this document. The on–orbit function requirements are discussed in the Man–Machine Operating Procedures section.

3 - 2

FIGURE 3.1.1.1–1 CYLINDER RETAINING

BRACKET/CLIP, LAUNCH STOWAGE MODE

FIGURE 3.1.1.1–2 CYLINDER RETAINING

BRACKET/CLIP, ON–ORBIT STOWAGE MODE

3 - 3

3.1.1.2 INTERFACE DESCRIPTION

3.1.1.2.1 MAN–MACHINE INTERFACE: ON–ORBIT STOWAGE MODE

A. The quick don (Q–D) mask will be attached and secured to the reducer/cylinder quick disconnect while stowed in the PBA locker. The crew members will have direct access to the red levers of the mask (manual harness inflation control levers ) after the locker door is opened. Direct access to the red levers is necessary for one–handed manipulation and donning of the quick don (Q–D) mask. Figure 3.1.1.2.1–1, Mask Holder/Mask Assembly, Access Area shows the location of the red levers.

FIGURE 3.1.1.2.1–1 MASK HOLDER/MASK ASSEMBLY, ACCESS AREA

B. The crew members will have enough clearance, in accordance with the requirements of SSP 50005, above the top of the reducer/cylinder assembly for activation of the oxygen cylinder on–off lever. See Figure 3.1.1.2.1–2, Reducer/Cylinder Mounted Assembly Access Area.

C. The reducer/cylinder assembly will be mounted to accommodate visual inspection of the pressure indicator on the face of the reducer, as shown in Figure 3.1.1.2.1–2, Reducer/Cylinder Mounted Assembly Access Area.

D. The reducer/cylinder assembly will be mounted in a manner that will allow the assembly to be pulled directly forward from the mount when being removed for emergency use.

E. The Mask Holder/Mask assembly will be mounted in a manner that will allow the assembly to be pulled directly forward from the mount when being removed for emergency use.

3 - 4

F. The Extension Hose/Tee Kit will be mounted with the mask in the Portable Emergency Provisions (PEP) locker.

G. The PBA will not require the use of any tools or accessories to change the PBA mounting from the launch stowage mode to the on–orbit stowage mode.

Y

Z X

FIGURE 3.1.1.2.1–2 REDUCER/CYLINDER MOUNTED ASSEMBLY ACCESS AREA

NOTE: 2.9 (MIN) DIMENSION IS FOR REFERENCE ONLY

3 - 5

3.1.1.2.2 MAN–MACHINE INTERFACE: OPERATING MODE

The PBA harness will attach to the crewmembers’ clothing at the waist using a belt clip or on the leg with an auxiliary elastic leg strap. The PBA will interface electrically with the Internal Audio System (IAS) components through a Lemo style audio connector. The crew will not require the use of tools to activate or de–activate the PBA system. The PBA will be capable of withstanding crew induced bump loads of 50 pounds force (lbf) over a 3/8” diameter area while operating and attached/harnessed to a crewmember.

3.1.1.2.3 LAUNCH STOWAGE MODE

A. The stowage configuration will not cause induced loads on the mask and hose assembly that would cause abnormal deformation to the mask shell. Abnormal deformation can cause material memory that may prevent positive sealing of the mask/face interface.

B. The stowage configuration will accommodate the extension hose/tee kit.

C. The PBA mask visor will be protected from abrasion caused by launch and on–orbit vibration loads.

D. The locker door will support loads that are induced during launch and on–orbit vibration and accelerations. Any locker deformation that results from launch loads will not preclude removal of the PBA from the stowed position.

3.1.1.3 INTERFACE RESPONSIBILITIES

All inter–module connections to the PBA will be similar in orientation, form, and function.

The module integrator must retain this responsibility.

3.1.1.3.1 OXYGEN ACCESS PORT

All interconnecting oxygen supply lines will be provided by the module integrator. Oxygen supply Quick Disconnects (QDs) will be supplied by the PEP Subsystem to the module integrator.

3.1.1.3.2 BRACKET INSTALLATION

Installation of the PBA mounting brackets to the inside of lockers or the faces of racks will be performed by the locker or module integrators.

3.1.1.3.3 EQUIPMENT MOUNTS

Any PBA unique equipment mounts and special mounting provisions will be provided by the PEP subsystem. Specifically, the Reducer/Cylinder Mount, Mask Holder, cable restraints, 3 - 6 and loop fastener will be supplied by the PEP Subsystem. Equipment mounts supplied by the PEP Subsystem for the PBA will not be considered as Orbital Replaceable Units (ORUs).

All secondary support structure will be provided by the locker or module integrator.

3.1.1.3.4 FASTENERS

All fasteners (captive or non–captive) used to mount PBA hardware to the locker or module will be provided by the locker or module integrator. PBA fasteners captive to the locker or module structure will be provided by the locker or module integrator. Non–captive fasteners are prohibited per SSP 50005, paragraph 11.9.3.1e, for on–orbit removable items.

3.1.1.4 COORDINATE SYSTEM

The Space Station module and rack coordinate systems are body–fixed systems as defined for the International Space Station in SSP 30219.

3.1.1.5 ENGINEERING UNITS, TOLERANCES, AND CONVERSIONS

Standard English units will be used on all PBA drawings. Equivalent Metric units will accompany English units on all interface documentation.

3.1.2 INTERFACE REQUIREMENTS

3.1.2.1 INTERFACE PLANE

The interface plane for the PBA to the ISS will be as shown in Figure 3.1.2.1–1, PBA to ISS Interface Plane (Stowage and Operating).

3.1.2.1.1 ENVELOPE INTERFACES

The stowed configuration of the PBA will have hardware footprints as shown in Figure 3.1.2.1.1–1, PBA Hardware Interface Footprints and Hole Patterns. The PBA enclosure will accommodate the hardware footprints as shown in Figures 3.1.2.1.1–2, Cylinder/Mount Bracket Envelope, 3.1.2.1.1–3, Mask Holder/Mask Envelope, and 3.1.2.1.1–4, Extension Hose/Tee Kit Envelope.

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FIGURE 3.1.2.1–1 PBA TO ISS INTERFACE PLANE

(STOWAGE AND OPERATING)

3 - 8

14.900

NTS NTS

NTS

.X = ± 0.10

.XX = ± 0.030

.XXX = ± 0.010

HOLE TO MATCH FASTENER DEFINED IN 3.1.2.4.1B

FIGURE 3.1.2.1.1–1 PBA HARDWARE INTERFACE FOOTPRINTS AND

HOLE PATTERNS

3 - 9

FIGURE 3.1.2.1.1–2 CYLINDER/MOUNT BRACKET ENVELOPE

3 - 10

FIGURE 3.1.2.1.1–4 EXTENSION HOSE/TEE KIT ENVELOPE

3.1.2.1.2 VOLUME CONFIGURATION

A. The enclosure will be free of sharp corners or edges per SSP 50005 that could puncture the PBA mask, harness, hoses, or cylinder during removal.

B. Door latch retainer brackets will not interfere with the on–orbit operation and access of the PBA hardware.

3.1.2.2 MASS PROPERTIES

The PBA locker will accommodate the mass properties of the PBA as shown in Table 3.1.2.2–1, Mass Properties of the PBA Components.

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TABLE 3.1.2.2–1 MASS PROPERTIES OF THE PBA COMPONENTS

Reducer/Cylinder Assy., Oxygen, Emergency Quick–Don Mask Assy., Oxygen

Harness Assy, Emergency Total PBA, Emergency, PEP

2.62 lb.

1.61 lb.

0.39 lb.

Total 4.62 lb.

1 per locker 1 per locker 1 per locker 1 per locker

Restraints for Mask Hose and Extension Hose/Tee Kit Mount Assy., Cylinder

Mask Holder Assy.

Total Locker Mount Kit, Emergency PBA

0.33 lb.

3.37 lb.

0.73 lb.

Total 4.42 lb.

1 per locker 1 per locker 1 per locker 1 per locker

QD Outlet Assy., Female, Oxygen, Total QD Outlet Assy., Female, Oxygen,

0.33 lb.

Total 0.66 lb.

2 per locker 2 per locker

Pouch Assy.

Extension Hose, Oxygen (30 ft.)

Tee Assy., Oxygen Total Extension Hose/Tee Kit

Total PBA Hardware Package

0.66 lb.

3.62 lb.

0.23 lb.

Total 4.52 lb.

14.22 lb.

1 per locker 1 per locker 1 per locker 1 per locker

1 Unit

3.1.2.3 STRUCTURAL INTERFACES

The PBA locker structure will provide structural support for the PBA at the attach points.

3.1.2.3.1 STRUCTURAL LOADS

When the PBA mass properties are as described in Table 3.1.2.2–1, the PBA center of gravity is as described in section 3.1.2.3.2. The Module Integrator will design the PBA installation to the worst case loads for each module.

3.1.2.3.2 CENTER OF GRAVITY

The PBA center of gravity (CG) will be located as shown in Figures 3.1.2.3.2–1, Cylinder/Mount Center of Gravity (CG), 3.1.2.3.2–2, Mask Holder/Mask Center of Gravity (CG), and 3.1.2.3.2–3, Extension Hose/Tee Kit Center of Gravity (CG), Table 3.1.2.3.2–1, Center of Gravity of PBA Assemblies defines the CG in coordinates relative to the PBA assemblies themselves.

TABLE 3.1.2.3.2–1 CENTER OF GRAVITY OF PBA ASSEMBLIES (Values in inches)

X Y Z

Mask & Mask Holder Assembly, including 6 ft. hose 0.0 3.0 2.0

Cylinder Bracket Assembly 0.0 13.2 1.3

Extension Hose & Tee Kit 0.0 3.5 2.0

3 - 12

FIGURE 3.1.2.3.2–1 CYLINDER/MOUNT CENTER OF GRAVITY (CG)

3 - 13

FIGURE 3.1.2.3.2–2 MASK HOLDER/MASK CENTER OF GRAVITY (CG)

FIGURE 3.1.2.3.2–3 EXTENSION HOSE/TEE KIT CENTER OF GRAVITY (CG)

3 - 14

3.1.2.4 MECHANICAL INTERFACES

3.1.2.4.1 INSTALLATION FASTENERS

The PBA locker will utilize three different types of fasteners as described below:

A. The first type of fastener (six per locker) is for securing the PBA Cylinder Mount plate to the PBA locker structure. Reference: The PBA Cylinder Mount is to be considered part of the locker ORU. The PBA Cylinder Mount plate will be attached using .1900–32UNJF–3 CRES or equivalent non captivated fasteners. The locker structure will incorporate a self–locking insert, in the pattern shown in Figure 3.1.2.1.1–1.

B. The second type of fastener (four per locker) is for securing the PBA mask/ holder assembly to the PBA locker structure. The fastener will be a non captive .164 diameter or equivalent screw and panel inserts in the pattern shown in Figure 3.1.2.1.1–1. Section A–A of Figure 3.1.2.1.1–1 describes the cross section of the mask holder at the screw locations.

The screws will be a countersink head of 100°. The maximum allowed torque on the screw is 8–10 in–lb.

C. The third fastener is used to secure the extension hose/tee kit in two locations. The loop fastener will be used to secure the extension hose/tee kit in place within the locker during the launch stowage mode. A loop fastener with adhesive backing configured as shown in Figure 3.1.2.1.1–1 will be used for this purpose. This fastener type will be used in conjunction with other packaging material to restrain the kit while in the locker launch configuration.

3.1.2.4.2 SUPPORTING STRUCTURE AND BRACKETS

The locker integrator will provide a continuous load path from the PBA supporting mounts/ brackets to the locker primary structure.

3.1.2.4.3 ELECTRICAL

The PBA mounting hardware does not require electrical bonding to any surface.

3.1.2.4.4 CLAMPING

Clamping to hold mechanical contacts will be provided by threaded fasteners.

3.1.2.4.5 ADHESIVE

All hook and loop fastener materials or hose restraints provided by the PEP Subsystem will include certified self–adhesive backing. The attaching surface will be clean of particles and grease film prior to installation.

3 - 15

3.1.2.4.6 EQUIPMENT RESTRAINT DURING LAUNCH

The extension hose/tee assembly kit and mask holder will be restrained during launch to prevent damage to equipment.

3.1.2.5 FLUID INTERFACES

The PBA’s connection with ISS’s Environmental Control and Life Support System (ECLSS) oxygen supply lines will be through a station–side female QD in the elements responsible for providing an oxygen interface. The interface pressure will be between 70 and 120 psia at 60° to 113° F, with a Maximum Expected Operating Pressure (MEOP) of 200 psia. Flowrates of

0.05 lbm per minute will be available. The ECLSS oxygen supply will provide three (3) lbm of oxygen supply for each crewmember through the QD ports. The PBA will have a male QD, NASA P/N SEG33105027–001, Carleton P/N F388–1319–1 (2 places), and Carleton P/N F664220170–1 in the following respective locations: Input side of the mask, input side of the tee assembly and input side of the reducer/cylinder assembly, and input side of the extension hose. The location of the station–side QD will provide available space for interface to the PBA Tee assembly and Extension Hose assembly.

All components will be compatible with 100% oxygen systems, and will be maintained clean and sealed from contaminants until use, by tethered dust caps.

The PEP Subsystem will provide the station–side female fitting will be mated with the O2 supply line. The female QD fitting will be similar to Carleton P/N F361–1971–1 Quick Disconnect, both in operation and physical dimension. The station–side female QD will be considered an ORU. On–orbit replacement will be possible; the O2 line will be controllable, to effect the replacement.

NASA GFE P/N SEG33105312–301 Quick Disconnect Assembly will be supplied to the contractor for Node 1 and Node 2. This part will include a male 1/8–27 NPT threads for interface to the supply line. The Node 1/Node 2 contractor will provide the mating assembly (female 1/8–27 NPT threads) and interfacing seals/compounds/lubricants.

NASA GFE P/N SEG33105312–303 Quick Disconnect Assembly will be supplied to the contractor for the Lab, Hab, and Airlock. This part will include Boeing P/N 683–16347–181 Flange for interface to the supply line. The Lab/Hab/Airlock contractor will provide the mating assembly (Boeing P/N 683–16347–183 Nut Flange Kit or equivalent) and interfacing seals/compounds/lubricants.

The Hab/Lab/Airlock Bulkhead QD will supply captive fasteners in the pattern described as follows: The pattern will consist of a clover leaf flange with three #10–32UNJF–3A fasteners evenly spaced (120° +/– .05°) on a bolt circle of 2.00 +/– 0.010 inch diameter. The

3 - 16 fasteners will float in holes of .213 +/– 010 inch diameter. The fasteners will protrude from the back of the flange a distance of .306 +/– .010 inches. The panel will require a pass–thru hole of .990, –0.000 inch diameter for clearance of the Gamah fitting and associated key ring. The key ring is the largest diameter component which must pass through the panel during installation. Engagement with PG supplied fasteners will be required. Illustration of pattern is shown in Figure 3–12.1 Quick Disconnect Assembly.

Additionally, the Hab/Lab/Airlock Bulkhead QD is expected to extend forward 1.55 +/– 0.10 inches from the face of the mating flange, and extend rearward 1.60 +/– 0.10 from the mating face of the flange. These are shown in Figure 3.1.2.5–1, Quick Disconnect Assembly.

3.1.2.6 ELECTRICAL INTERFACES

3.1.2.6.1 ELECTRICAL / COMMUNICATION INTERCONNECT

The PBA will interface with the unique dedicated communication ports on the Headset Control Unit (HCU). The PBA communication interfaces will be as shown in Figure 3.1.2.6.1–1, PBA Communication Interface.

JEM

Node 1

Node 2

HAB

LAB

MPLM

Audio

Distribution Bus

ATU

Audio Terminal

Unit

Headset Control Unit

HCU

PBA Communication Crew Communication Headset

CCH

Headset

PBACH

FIGURE 3.1.2.6.1–1 PBA COMMUNICATION INTERFACE

3 – 17

FIGURE 3.1.2.5–1 QUICK DISCONNECT ASSEMBLY

3 - 18

3.1.2.6.2 CONNECTOR PIN ASSIGNMENTS

The PBA pin assignments for its electrical connector will be as shown in Table 3.1.2.6.2–1, Interface Characteristics Between PBA and HCU. The interfacing electrical connector J1 will be a Lemo type in–line connector plug as shown in drawing number 2000 166–105 or equivalent. This connector interfaces with a female receptacle 2000 166–104, or equivalent.

TABLE 3.1.2.6.2–1 INTERFACE CHARACTERISTICS BETWEEN PBA AND HCU

Signal Name Signal Level Load Impedance

Connector Pin Number

Cable Type

Headphone Receiver

Headphone High

0 –30 dBm 600 ohms 1 Twisted Pair

Headphone Receiver

Headphone Low

0 –30 dBm 600 ohms 2 Twisted Pair

Not Used Spare N/A N/A 3 N/A

Microphone Microphone Shield

Signal Ground

4 Shielded Twisted Triple

Microphone Microphone High

–46 dB m nominal (1)

600 ohms 5 Shielded Twisted Triple

Microphone Microphone Low

Signal Ground

6 Shielded Twisted Triple

Microphone Microphone

PWR

+5 VDC <=3 mA rms 7 Shielded Twisted Triple

NOTES:

(1) Nominal => an output signal that will be produced by an average American male who is speaking into a microphone at a normal speech level (90 dB SPL).

3.1.2.6.3 INTERCONNECT DIAGRAM

The PBA has an electrical connection to the HCU. The PBA interconnection characteristics are shown in Table 3–3, per SS–CM–465 and SSP 30260:019, ATU ICD. The communication equipment will operate at voltages of 5 V dc.

3 - 19

3.1.2.6.4 ELECTRICAL CONNECTOR SPECIFICATIONS

The PBA communication connector will be in accordance with the components specified in SSQ 25002. This connector will be prequalified by the ISS Prime before incorporation into the final design.

3.1.2.7 ENVIRONMENTS

The PBA will be qualified to operate under the environmental conditions specified below:

3.1.2.7.1 THERMAL

3.1.2.7.1.1 NON–OPERATING

The PBA will operate after being exposed to air temperatures ranging from –45° F to 150° F.

3.1.2.7.1.2 ON–ORBIT OPERATING

While on–orbit, the PBA will operate while being exposed to ambient air temperatures ranging from 60° F to 85° F.

3.1.2.7.1.3 AMBIENT COOLING

The PBA assembly touch surfaces will not exceed 113° F.

3.1.2.7.2 PRESSURE

3.1.2.7.2.1 OPERATING

The on–orbit ambient operating pressure for the PBA will be from 3.5 psia to 15.2 psia.

Operation of the communications components will only be required between the range of 9 to 15.2 psia.

3.1.2.7.2.2 NON–OPERATING

The PBA will be able to return to normal operation after de–pressurization to 1.9 x10E–7 psia and return to operating temperature and pressure.

3 - 20

3.1.2.7.2.3 DE–PRESSURIZATION / RE–PRESSURIZATION

A. The PBA will be able to return to normal operation after being exposed to a de–pressurization rate no greater than 18 psia/minute.

B. The PBA will be able to return to normal operation after being exposed to a re–pressurization rate no greater than 3.0 psia/minute.

C. The PBA will be capable of tolerating the differential pressure of de–pressurization and re–pressurization without resulting in a hazard or failure propagation.

3.1.2.7.3 AMBIENT HUMIDITY

3.1.2.7.3.1 ON–OPERATING

The PBA will be designed to survive in an ambient humidity environment ranging from 0.0% to 100% relative humidity.

3.1.2.7.3.2 ON–ORBIT OPERATING

The PBA will operate in an ambient humidity environment with dew points of 35° F to 70° F (25% to 75% relative humidity) at temperatures in the range of 0° F to 120° F.

3.1.2.7.4 ACCELERATION

The PBA will withstand the steady state accelerations described in Table 3.1.2.7.4–1, Secondary Structure Steady State Acceleration at all physical interfaces with the locker. The accelerations are to be combined with the random vibration environments in Table 3.1.2.7.5.1–1 as discussed in SSP 30559.

TABLE 3.1.2.7.4–1 SECONDARY STRUCTURE STEADY STATE ACCELERATION

(IN ORBITER COORDINATE SYSTEM)

ACCELERATION

DIRECTION

LIFTOFF

G’S

LANDING

G’S

X Y Z

+ 13.6 + 11.0 + 8.0

+ 12.2 + 12.9 + 8.7

3.1.2.7.4.1 NON–OPERATING

The PBA, when installed in the mounting bracket, will operate after exposure to the accelerations shown in Table 3.1.2.7.4–1.

3 - 21

3.1.2.7.4.2 ON–ORBIT OPERATING

While on–orbit, the PBA will operate during exposure to accelerations of 0.4 g’s in any direction.

3.1.2.7.5 VIBRATION

3.1.2.7.5.1 NON–OPERATING

The PBA will operate after exposure to the maximum vibration shown in Table 3.1.2.7.5.1–1, Random Vibration Environments for Equipment Design.

TABLE 3.1.2.7.5.1–1 RANDOM VIBRATION ENVIRONMENTS

FOR EQUIPMENT DESIGN

LOCATION FREQUENCY LEVEL

Input to endcone–mounted equipment 20 Hz

20–80 Hz 80–350 Hz

350–2000 Hz 2000 Hz

Composite

0.01 g^2/ Hz +3.0 dB/Octave

0.04 g^2/ Hz –3.0 dB/Octave

0.007 g^2/ Hz

6.1 grms

3.1.2.7.5.2 ON–ORBIT OPERATING

While on–orbit, the PBA will not produce vibrations.

3.1.2.7.6 ELECTROMAGNETIC EFFECTS

3.1.2.7.6.1 ELECTROMAGNETIC COMPATIBILITY

The PBA will be designed to be electromagnetically compatible within itself and with all other designed interface equipment. The PBA will meet the requirements of SSP 30243.

3.1.2.7.6.2 ELECTROMAGNETIC INTERFERENCE

The PBA will meet the requirements of SSP 30237 and SSP 30238.

3.1.2.7.6.3 BONDING

The PBA mounting hardware does not require electrical bonding to any surface.

3 - 22

3.1.2.7.7 ACOUSTIC

The PBA will operate during and after exposure to the acoustic spectrum of Table 3.1.2.7.7–1, ISS Element Internal Acoustic Spectrum.

TABLE 3.1.2.7.7–1 ISS ELEMENT INTERNAL ACOUSTIC SPECTRUM

1/3 Octave Band Center Frequency

(HZ)

Sound Pressure Level (dB) rev. 2X10–5 N/m2

1/3 Octave Band Center Frequency

(HZ)

Liftoff Aeronoise

31.5 40.0 50.0 63.0 80.0

100.0 125.0 160.0 200.0 250.0 315.0 400.0 500.0 630.0 800.0 100.0

1250.0 1600.0 2000.0 2500.0 3150.0 4000.0 5000.0 6300.0 8000.0

10000.0

106.0 109.0 111.5 114.0 116.0 117.0 118.5 119.0 119.0 118.0 117.5 115.5 112.5 109.5 107.0 103.0 99.5 95.5 91.5 88.0 83.0 79.0 74.5 70.0 66.0 60.0

96.0 99.5

102.0 105.0 108.0 110.0 112.0 113.5 115.0 116.0 116.5 114.5 111.0 107.5 104.5 101.5 97.5 94.0 90.0 86.5 82.0 77.0 73.0 68.0 63.0 57.5

Overall 127.5 123.5

Duration: 60 seconds + 30 seconds per mission

3 - 23

4.

5”

R A

D

0.

5”

R A

D

FIGURE 3.1.2.1.1–3 MASK HOLDER/MASK ENVELOPE

A - 1

APPENDIX A ABBREVIATIONS AND ACRONYMS

A.1 ABBREVIATIONS AND ACRONYMS

ACA Associate Contractor Agreement

ASI Agencia Spatiale Italiano

ASTM American Society for Testing and Materials

ATU Audio Terminal Unit

CCB Configuration Control Board

CCH Crew Communications Headset

CCP Configuration Control Panel

CG Center of Gravity

CSA Canadian Space Agency

CTSD Crew and Thermal Systems Division

cu. ft. cubic feet dB(A) decibel A weighted

DR Discrepancy Report

ECLSS Environmental Control and Life Support System

EMC Electromagnetic Compatibility

EMI Electromagnetic Interference

ESA European Space Agency

FCSD Flight Crew Support Division

FSE Flight Support Equipment

GFE Government Furnished Equipment

GHE Ground Handling Equipment gm gram

GSE Ground Support Equipment

HCU Headset Control Unit

HZ Hertz

IAS Internal Audio System

ICD Interface Control Document

IMS Inventory Management System

A - 2

ISS International Space Station

ISSA International Space Station Alpha

ISS ICWG International Space Station Interface Control Working Group

IVA Intravehicular Activity

JSC Johnson Space Center

JSCM Johnson Space Center Manual lb pound lpm liters per minute

MEOP Maximum Expected Operating Pressure

MIL Military min minute

MRR Mission Reconfiguration Request

MTBF Mean Time Between Failure

NAS National Aircraft Standard

NASA National Aeronautics and Space Administration

NASDA National Space Development Agency of Japan

NHB NASA Handbook

O2 Oxygen

ORU Orbital Replaceable Unit

OTSE Off–the–shelf Equipment

PBA Portable Breathing Apparatus

PBACH Portable Breathing Apparatus Communications Headset

PDA Pre–delivery Acceptance

PEP Portable Emergency Provisions

PHS&T Packaging, Handling, Shipping, and Transportation

PIRN Preliminary Interface Revision Notice

PRD Program Requirements Document

PRR Program Requirements Review

A - 3 psi pounds per square inch psia pounds per square inch absolute psig pounds per square inch gauge

Q–D Quick Don

QA Quality Assurance

QD Quick Disconnect rms root mean square

RSA Russian Space Agency

S/AD Specification and Assembly Drawing scfm standard cubic feet per minute

SDID Supporting Development Implementation Document

SPL Sound Pressure Level

SR&QA Safety, Reliability, and Quality Assurance

SSP Space Station Program

STD Standard

TBD To Be Determined

TPS Test Preparation Sheet vol volume

°F degree Fahrenheit

B–1

APPENDIX B DETAILED DRAWINGS

DRAWING PAGE

SIG3310500 DRAWING TREE B–2

SEG33105002 PORTABLE BREATHING APPARATUS ASSEMBLY B–4

SDG33105027 FITTING, ELBOW B–5

SEG33105010 REDUCER / CYLINDER ASSEMBLY B–6

SEG33105011 CYLINDER ASSEMBLY B–7

SEG33105020 QUICK DON MASK ASSEMBLY B–8

SEG33105030 HARNESS ASSEMBLY B–9

SEG33105050 MOUNT ASSEMBLY, CYLINDER B–10

SEG33105051 TOP MOUNT ASSEMBLY, CYLINDER MOUNT B–11

SEG33105060 BOTTOM MOUNT ASSEMBLY, CYLINDER MOUNT B–12

SDG33105064 ATTACHMENT PLATE, CYLINDER MOUNT B–13

SEG33105316 MASK HOLDER ASSEMBLY B–14

SEG33104995 EXTENSION HOSE / TEE KIT ASSEMBLY B–15

SEG33105101 EXTENSION HOSE ASSEMBLY, OXYGEN B–16

SEG33105309 TEE ASSEMBLY, OXYGEN B–17

SEG33105312 QUICK DISCONNECT ASSEMBY, ECLSS B–18

B–2

SIG33105000

DRAWING TREE

(SHEET 1)

FIGURE B–1A DRAWING TREE (1)

B–3

SIG33105000 DRAWING TREE

(SHEET 2)

FIGURE B–1B DRAWING TREE (2)

B–4

Fig B–2 PBA ASSEMBLY

SEG33105002

PORTABLE BREATHING APPARATUS ASSEMBLY

Fig B–3 Fitting, Elbow

B–5

SDG33105027

FITTING, ELBOW

B–6

Fig B–4 Reducer/ Cylinder Assembly

SEG 33105010

REDUCER / CYLINDER ASSEMBLY

Fig B–5 Cylinder Assembly

B–7

SEG33105011

Fig B–6 Q–D Mask Assembly

B–8

SEG33105020

QUICK DON MASK ASSEMBLY

Fig B–7 Harness Assembly

B–9

SEG33105030

HARNESS ASSEMBLY

Fig B–8 –301 Mount Assembly

B–10

Fig B–9 Top Mound Assembly, Cylinder Mount

B–11

SEG33105051

Fig B–10 Bottom Mount Assembly, Cylinder Mount

B–12

SEG33105060

BOTTOM MOUNT ASSEMBLY, CYLINDER MOUNT

N O

T E

T he th ic kn es s of th e bo tto m m ou nt a ss em bl y is

.1 in ch es . B ac k pl at e an d bo tto m m ou nt a re th e sa m e m at er ia l, –T

A l A ly

T he b ot to m m ou nt is c oa te d w ith p ol yu re th an e in th e ar ea in w hi ch th e cy lin de r re st s.

TO:

Fig B–11 Attachment Plate, Cylinder Mount

B–13

SDG33105064

ATTACHMENT PLATE, CYLINDER MOUNT

Fig B–12 Mask Holder Assembly

B–14

SEG33105316

MASK HOLDER

ASSEMBLY

N O

T E

T he m as k ho ld er is m ad e of

U lte m

0.

TO:

Fig B–13 Extension Hose/Tee Kit Assembly

B–15

SEG33104995

EXTENSION HOSE / TEE KIT ASSEMBLY

Fig B–14 Extension Hose Assembly, Oxygen

B–16

SEG33105101

EXTENSION HOSE ASSEMBLY, OXYGEN

Fig B–15 Tee Assmebly, Oxygen

B–17

SEG33105309

TEE ASSEMBLY, OXYGEN

Fig B–16 Q–D Assembly, ECLSS

B–18

SEG33105312

QUICK DISCONNECT ASSY, ECLSS