IGF::OT::IGF MEET TSO-C70A STANDARDS FOR TYPE II LIFE RAFTS WITH FOLLOWING VARIANCES: NO NEED FOR FAA DISSEMINATION OF RAFT DATA DUE TO R&D NATURE OF HARDWARE MATERIALS TESTING (6.1) WAIVED UNDER THIS SOW DUE TO R&D NATURE UNLESS NEEDED TO VERIFY NEW MATERIALS APPLICABILITY TO THIS APPLICATION RAFT TESTING (6.2.3) WAIVED UNDER THIS SOW DUE TO R-D NATURE TEMPERATURE EXPOSURE AND INFLATION (6.2.5) TESTING WAIVED UNDER THIS SOW DUE TO R&D NATURE MASS LESS THAN30IBS. (EXCLUDING ANY MOUNTING HARDWARE). NOTE: THE LOWER A RAFT ASSEMBLY MASS, THE HIGHER LEVEL OF BENEFIT FOR THE CREW SURVIVAL ENGINEERING TEAM. EFFORTS SHOULD BE MADE TO MAKE THE RAFT MASS AS LIGHT AS POSSIBLE. TOTAL PACKED VOLUME LESS THAN 2767.5 INC NOTE THE SMALLER THE VOLUME, THE HIGHER LEVEL OF BENEFIT FOR THE CREW SURVIVAL ENGINEERING TEAM. EFFORTS SHOULD BE MADE TO MINIMIZE THE VOLUME AS MUCH AS POSSIBLE UNDER THE MAXIMUM LIMIT. TOTAL PACKED VOLUME PLUS STOWAGE MOUNTING OPTIONS MUST FIT WITHIN 4292.00 CU. IN. GEOMETRIC VOLUME AS SPECIFIED BY NASA-PROVIDED VOLUMETRIC SHAPE/MODEL SURVIVAL EQUIPMENT NOT REQUIRED AND SHOULD NOT BE PACKED IN RAFT MINIMUM OF 19.6 SQUARE FEET OF FLOOR WITHIN RAFT WHEN DEPLOYED. CAPABLE OF SUPPORTING TOTAL OCCUPANCY WEIGHT OF 1140 LBS. 20 LBS. MATERIALS AND DESIGN SHOULD BE COMPATIBLE WITH LONG TERM EXPOSURE TO VACUUM (ASSUME 10 5 TORR) WITH STEADY STATE TEMPERATURE AT VACUUM NOT TO EXCEED 85F ASSUMED MAX RATE OF DEPRESS FROM NOMINAL PRESSURE (14.7 TO VACUUM (0 PISA) IS -30.0 PSI/MIN LANDING LOADS TOLERANCE OF 55G ACCELERATION FORCE (EXCLUDING MOUNTING PROVISIONS) BOTTLE GAS SHOULD BE INERT, NON-TOXIC GAS (PREP NITROGEN OVER CO2). THE LIFE RAFT HARDWARE SHALL CONSIST OF A RAFT PRESSURE VESSEL OR VESSELS, COMPRESSED GAS INFLATION CANISTER, INFLATION MECHANISM, AND SOFT VALISE OR HARD OUTER CASING/ENCLOSURE. THE HARDWARE DEVELOPED SHALL BE FABRICATED AND TESTED PER RELEVANT TSO-C70A AND INTEGRATION SPECIFICATIONS. AN INFORMAL COMPILATION OF DESIGN DATA INCLUDING FINAL HARDWARE MASS, VOLUME AND PRO E MODELS FOR THE ASSEMBLIES SHALL BE DELIVERED TO THE CREW AND THERMAL SYSTEMS DIVISION AT JSC WITH THE PROTOTYPE HARDWARE. THE PRO E MODELS SHALL BE IN SUFFICIENT DETAIL TO BE INTEGRATED WITH THE MPCV CABIN INTERIOR SOLID MODEL DESIGNED BY NASA AND VEHICLE CONTRACTOR.