NASA/Goddard Space Flight Center, Code 284.8, Greenbelt, MD 20771

99 -- SPACECRAFT ORBIT INSERTION SOLID PROPELLANT ROCKET MOTOR SOL 03306 POC Charles A. Greene, Contracting Officer, 301-286-6013. THIS Is A NOTICE OF INTENT TO ISSUE A REQUEST FOR PROPOSAL (RFP) 5-03306/541 On OR ABOUT APRIL 10, 1995, ON A SOLE SOURCE BASIS TO THIOKOL CORPORATION FOR An ORBIT INSERTION SOLID PROPELLANT ROCKET MOTOR FOR THE EQUATOR-S SPACECRAFT. The ROCKET MOTOR SHALL CONTAIN An IGNITER AND SAFE AND ARM MECHANISM AND SPACECRAFT INTERFACE RING. MINIMUM ROCKET MOTOR REQUIREMENTS, DERIVED FROM The EQUATOR-S SPACECRAFT REQUIREMENTS, ARE As FOLLOWS: (A) PHYSICAL REQUIREMENTS (NOMINAL): (1) Total LENGTH (INCLUDING NOZZLE): 22.88 INCHES: (2) LOADED WEIGHT: 84LBM; (3) BURN-Out WEIGHT: 10LBM; (4) DIAMETER: 13.52 Inches; (B) BALLISTIC REQUIREMENTS (70 DEGREE F VACUUM): (1) MAXIMUM THRUST: 1780 LBF; (2) MINIMUM Total IMPULSE: 21,050 LBF-SEC; (3) MAXIMUM BURN TIME: 16.2 Sec; (4) MAXIMUM THRUST MISALIGNMENT: 0.5 Degrees; (C) INTERFACE REQUIREMENTS: (1) INTERFACE RING Bolt HOLE PATTERN: 8 x 0.250-28UNF-2B EQUALLY SPACED ON 10.120 INCH DIAMETER. ATTACHMENT FLANGE 1.330 INCH AFT Of FORWARD DOME; (D) OPERATING ENVIRONMENT REQUIREMENTS: (1) OPERATING TEMPERATURE Range: 20 TO 120 DEGREES F; (2) STORAGE TEMPERATURE RANGE: 0 To 120 DEGREES F; (3) ACCELERATION: 10 G'S; (4) VIBRATION: 1.0 G ANY AXIS. This ITEM NEEDS TO BE DELIVERED BY DECEMBER 1996 TO SUPPORT An EARLY 1997 LAUNCH. PURSUANT TO 10 U.S.C. 2304(C)(1), THIOKOL CORPORATION Is THE ONLY RESPONSIBLE SOURCE CAPABLE Of PERFORMING THIS EFFORT WITHIN THE REQUIRED TIMEFRAME. Any OTHER PERSONS DESIRING CONSIDERATION ARE REQUIRED To FULLY IDENTIFY THEIR INTEREST AND CAPABILITIES IN WRITING WITHIN FIFTEEN (15) DAYS Of THE PUBLICATION OF THIS SYNOPSIS TO THE GSFC CONTRACTING OFFICER LISTED ABOVE. No TELEPHONE REQUESTS. See Numbered Note(s): 12, 22. (0080)

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