the x and z velocity channels. As a result, the missile impacted about 12 miles
     short and 0.2 miles right of target.
170. 52F (Tall Tree 4), 23 Mar 63, Response Mode 4, Flight Phase 1: Missile self-
     destructed at about 91 seconds for unknown reasons. Impact was near the flight
     line about 120 miles downrange.
171. 65E (Black Buck), 24 Apr 63, Response Mode NA, Flight Phase 2.5: Vernier
     hydraulic-system pressure was lost at 301 seconds, resulting in loss of vernier-
     engine control during the vernier solo phase. The reentry vehicle impact point
     was not perceptibly affected by this malfunction.
176. 139D LV-3A/ Agena B (Big Four), 12 Jun 63: Response Mode 4T, Flight Phase 1:
     Flight appeared normal until about 88.4 seconds when, due to a hydraulic failure,
     the vehicle made a violent right and down maneuver. The missile broke up five
     seconds later at 93.4 seconds.
181. 24E (Silver Doll), 26 July 63, Response Mode 4, Flight Phase 2: Spurious voltage
     transients caused premature pressurization of the vernier solo tanks at
     101.3 seconds, and premature sustainer engine shut down just after booster
     separation at 141 seconds.
187. 63D (Cool Water III), 6 Sep 63, Response Mode 4, Flight Phase 1: All systems
     performed satisfactorily till 110 seconds, when the sustainer/vernier hydraulic
     pressure dropped from 3080 to 490 psig. The failure resulted in premature
     shutdown of the sustainer engine at 136 seconds. Booster-engine cutoff occurred
     normally at 140.3 seconds, and the booster was successfully jettisoned. The
     impact point occurred about 620.miles downrange.
188. 84D (Cool Water IV), 11 Sep 63, Response Mode 4T, Flight Phase 2~5: Flight
     seemed normal through SECO, although the pneumatic precharge to the vernier
     solo accumulator was lost at 96.6 seconds. Due to this failure, missile stability was
     lost near the start of the vernier solo phase. The R/V probably failed to separate.
189. 71E (Filter Tip), 25 Sep 63, Response Mode 4T, Flight Phase 2: Visual observers
     reported a boat-tail fire, radical oscillations in yaw, and rough running booster
     and sustainer engines. Failure of the sustainer hydraulic system during the
     staging sequence resulted in loss of missile stability at 140 seconds. Sustainer and
     vernier engines shut down at about 267 seconds with the impact point about 600
     miles downrange.
190. 45F (Hot Rum), 3 Oct 63, Response Mode 1, Flight Phase 1: The B-1 booster-engine
     fuel valve failed to open during the start sequence, so the engine did not ignite.
     Missile toppled over and exploded.




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