240. 156D, 2 Mar 65, Response Mode 1 Flight Phase 1: At 0.36 seconds booster fuel-
     pump pressure dropped due to a fuel prevalve failure, booster lost thrust, fell
     back on launch pad, and was destroyed at 3.26 seconds.
251. 68D/ABRES (Tennis Match), 27 May 65: Response Mode 4, Flight Phase 1: A
     failure in the booster gas-generator loop resulted in decreasing booster
     performance after 116 seconds. The impact point stopped moving at 122 seconds
     when an explosion occurred in the thrust section. Further vehicle breakup
     occurred at 218 seconds. Destruct was sent at 293 seconds. Debris impacted close
     to the intended ground track.
257. SLV-3/Agena D (White Pine), 12 Jul 65: Response Mode 4 & 5, Flight Phase 2 & 3:
     Flight was normal until booster engines cutoff at 131 seconds. As a result of a
     circuit board failure caused by excessive vibrations, the sustainer also shutdown
     at BECO. The Atlas booster engines did not separate immediately from the
     sustainer, but did so some 50 seconds later after the event timer recycled. The
     Agena subsequently separated and ignited at about 198 seconds, creating wild
     uprange movements on the IP display by 255 seconds. Destruct was sent at 257
     seconds.
267. SLV-3 (GTV-6), 25 Oct 65, Response Mode 4, Flight Phase 3: The flight was a
     failure although all Atlas objectives were achieved. The Agena startup appeared
     normal, but the engine shut down after about one second of operation,
     Propellants ceased flowing but the helium pressurization system continued to
     pressurize the propellant tanks until they burst.
276. 303D (Eternal Camp), 4 Mar 66, Response Mode 5, Flight Phase 1: Although track
     and rate lock were lost at 88 seconds, missile appeared normal till about 112
     seconds when skyscreen operator reported that vehicle was spiraling. A
     hydraulic system failure occurred during the staging sequence, resulting in loss of
     vehicle stability at 153 seconds and sustainer engine shutdown at 194 seconds.
     The impact point initially appeared to stop about 800 miles downrange, well
     beyond the booster impact point. At about this time or shortly thereafter,
     telemetry indicated rapidly varying pitch, roll, and yaw rates and shutdown of
     sustainer and vernier engines. Final impact was estimated to be 976 miles
     downrange and 3° left of the nominal track.
279. 304D (White Bear), 19 Mar 66, Response Mode 5, Flight Phase 2: The reentry
     vehicle impacted 82 miles beyond the target point when the head suppression
     valve failed to close at SECO. The LOX tank thus vented through the sustainer
     chamber, adding impulse in the process.
281. 184D (AC-8) ,7 Apr 66, Response Mode 4T, Flight Phase 4: Flight appeared normal
     until second Centaur burn. Both Centaur engines started but one could not



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