96.   ITOS:-E (WTR), 16 July 73, Response Mode 4T, Flight Phase 2: Pump-motor failure
      during second-stage bum at 490 seconds resulted in loss of hydraulic pressure,
      loss of attitude control, and vehicle tumbling.

100. Skynet IIA, 19 Jan 74, Response Mode NA, Flight Phase 4 and 5: Flight was within
     normal limits until impact point passed through Africa gate. During the second
     bum of the second stage, a short circuit in the second-stage electronics package
     resulted· in an improper spacecraft orbit. The satellite reentered the earth's
     atmosphere five days later on 24 Jan 74.
101. WESTAR-B, 13 Apr 74, Response Mode NA, Flight Phase 1: One solid-rocket
     motor carried to MECO, but mission was still a complete success.

102. SMS-A, 17 May 74, Response Mode NA, Flight Phase 1 and 5: Mission was a
     partial success, although low first-stage velocity resulted from a liquid oxygen
     pressure line failure, and a booster shroud that snagged before fully jettisoning.
     Apogee was some 1,767 miles below the planned· value, and well outside three-
     sigma limits.

130. ESRO-GOES, 20 Apr 77, Response Mode NA, Flight Phase 2.5 and 5: Due possibly
     to a short circuit in· the second stage or failure in one of the two explosive bolts
     that hold the stage 2/3 clamp band together, the third stage separated
     prematurely from the second stage while spinning at only two rpms instead of the
     normal 97 rpms. As a result, coning during third-stage bum resulted in a
     spacecraft apogee nearly 13,000 miles low, and far outside three-sigma limits.
134. OTS, 13 Sep 77, Response Mode 4, Flight Phase 1: Core vehicle exploded at 57
     seconds due to a burn through on the forward end of the #1 Castor IV motor.
155. DJr, 3 Aug 81, Response Mode NA, Flight Phase 2 and 5: Flight was considered a
     success, although a 260-pound deficiency in fuel loading led to a premature
     propellant-depletion shutdown of the second bum of the second stage and
     degradation of final orbit. The inertial velocity at SECO was 240 ft/ sec lower than
     planned. Final apogee was some 855 miles too low and well outside three-sigma
     limits.
162. WESTAR-V, 9 June 82, Response Mode NA, Flight Phase 1: Booster performance
     was low but mission was a success. Apogee and perigee were within three-sigma
     limits.

178. GOES-G, 3 May 86, Response Mode 4, Flight Phase 1: An electrical short in a
     control circuit in first-stage relay box caused premature main-engine shutdown at
     71 seconds. Vehicle then tumbled and was broken up by aerodynamic forces.
     RSO sent destruct at approximately 91 seconds.




9/10/96                                   144                                        RTI