Department of the Air Force Report, 1996

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191. 163D (Cool Water V), 7 Oct 63, Response Mode 4, Flight Phase 1: Flight was
normal up to about 73 seconds when the missile exploded. Suspected cause was
intermediate bulkhead reversal/rupture due to insufficient helium pressure.
194. 136F (ABRES), 28 Oct 63, Response Mode 4T, Flight Phase 2: After a normal
booster phase and staging, failure of sustainer hydraulic system resulted in loss of
sustainer control and stability at 138 seconds. Sustainer and vernier engines shut
down at 260 seconds, some 28 seconds early. The R/V impacted about 507 miles
downrange.
196. 158D (Cool Water VI)., 13 Nov 63, Response Mode 4, Flight Phase 1: The trajectory
was low throughout flight. The sustainer/vernier hydraulic pressure was lost at
112.7 seconds, followed by missile self-destruct at about 118 seconds when the
vacuum impact point was about 280 miles downrange and on azimuth.
202. 48E (Blue Bay), 12 Feb 64, Response Mode 4, Flight Phase 2: The booster engine
shut down at 119.5 seconds, and the sustainer engine shut down prematurely at
198.8 seconds. Impact was near the flight line about 635 miles downrange.
207. 3F (High Ball), 3 Apr 64, Response Mode 1, Flight Phase 1: Missile was destroyed
on the pad when the Bl booster engine failed to ignite.
212. 135D (AC-3), 30 June 64, Response Mode 4, Flight Phase 3: The Centaur engines
shut down early, apparently due to a hydraulic coupling failure that led to a
failure in the propellant system. Impact was about 2340 miles downrange.
219. 57E (Gallant Gal), 27 Aug 64, Response Mode 4, Flight Phase 2: Missile
experienced an early SECO with no vernier bum thereafter due to a guidance-
system malfunction. Impact was about 88 miles short and 0.4 miles right of
target.
227. 289D (Mariner-3),5 Nov 64; Response Mode 4, Flight Phase 4: A short second burn
of the Agena prevented attainment of the desired orbit, and resulted in a
heliocentric orbit.
232. 146D., 11 Dec 64, Response Mode NA, Flight Phase 5: Flight was completely
normal through Centaur first bum. During the coast phase, liquid hydrogen
vented through the vent valve caused vehicle instability and tumbling. By second
engine firing, insufficient liquid hydrogen remained at boost-pump· sump to
sustain normal combustion.
236. 172D/ABRES (Beaver's Dam), 21 Jan 65: Response Mode 4, Flight Phase 2 and 3:
The Atlas apparently performed normally, except that the sustainer shut down
1.35 seconds early. The OVl"l failed to·separate from the Atlas and thus failed to
put the spacecraft in orbit.
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