94.3 seconds. A thrust-section fire before 20 seconds apparently failed the lube oil
     system, which led to cessation of propellant flow.
156. 131D LV-3A/ Agena B (Bargain Counter), 17 Dec 62, Response Mode 4T, Flight
     Phase 1: Mission failed because of an Atlas hydraulic failure. Missile lost stability
     at 77.5 seconds, then rolled clockwise, pitched down and yawed left before
     breaking up at about 80.5 seconds.
157. 64E (Oak Tree), 18 Dec 62, Response Mode 4T, Flight Phase 1: The B2 engine
     failed at 37.1 seconds as a result of lubrication loss to the pinion gear. Booster
     engine shutdown resulted in· a violent rolling yaw maneuver that caused missile
     breakup followed by an explosion at about 38 seconds.

158. 160D (Fly High), 22 Dec 62, Response Mode 4, Flight Phase 2: Due to noisy data,
     range safety limits in the automatic cutoff system were exceeded, causing
     generation of an· all-engines-cutoff signal. As a result, the vernier engines were
     cut off about 10 seconds early, and the reentry vehicle was about 12.3 miles short.
159. 39D (Big Sue), 25 Jan 63, Response Mode 4, Flight Phase 1: Propulsion system
     performance was unsatisfactory after 78 seconds, when booster engine
     performance started to decay. Booster engines shut down· shortly after this,
     probably as a result of excessive heating in the gas-generator regulator. The
     sustainer operated normally until at least 106 seconds, with shutdown occurring
     sometime between 106 and 126 seconds. Breakup· occurred about 300 seconds.
     Missile apparently impacted about 100 miles downrange.
164. 102D (Tall Tree 3), 9 Mar 63, Response Mode 5, Flight Phase 1: A flight-control
     malfunction occurred at about 15 seconds at the start of the pitch program. The
     missile pitched excessively, reaching 310° and an altitude of 5,000 feet at
     33.5 seconds when it broke up. Debris impacted close to pad.
166. 64D (Tall Tree 1), 15 Mar 63, Response Mode 4T, Flight Phase 2: A sustainer
     hydraulic-system failure at 83.5 seconds resulted in loss of sustainer engine
     control by 86 seconds and loss of vernier control at 99 seconds. Missile control
     was maintained by the booster engines until booster cutoff, when lack of sustainer
     and vernier control caused the missile to roll clockwise, pitch up, and yaw left.
     Sustainer thrust decayed at 131 seconds, and the missile began tumbling at
     136.6 seconds. Missile self-destructed at 146 seconds with impact point about 600
     miles downrange.

168. 193D (Leading Edge), 16 Mar 63, Response Mode 4T, Flight Phase 2: Loss of B2
     pitch feedback signal at 103.5 seconds resulted in loss of vehicle stability. Missile
     tumbled, then self-destructed at about 270 seconds.
169. 83F (Kendall Green), 21 Mar 63, Response Mode 4, Flight Phase 2.5: A defective
     solder joint apparently led to two instances of erroneous velocity computations in


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