131. LV-3A/ Agena B (Rubber Gun), 17 June 62, Response Mode 4, Flight Phase 3:
     Although Atlas performance was satisfactory, the mission was apparently a
     failure. No other data available.
134. 67E (Extra Bonus), 13 July 62, Response Mode 4, Flight Phase 2 and 2.5: A LOX
     leak in the high-pressure line apparently froze sustainer control components.
     Residual sustainer thrust after cutoff continued for some 30 seconds, causing a
     120-mile overshoot.
137. 145D (Mariner R-1), 22 July 62, Response Mode 5, Flight Phase 2: Booster stage
     and flight appeared normal until after booster staging at guidance enable at about
     157 seconds. Operation of guidance rate beacon was intermittent. Due to this and
     faulty guidance equations, erroneous guidance commands were given based on
     invalid rate data. Vehicle deviations became evident at 172 seconds and
     continued throughout flight with a maximum yaw deviation of 60° and pitch
     deviation of 28° occurring at 270 seconds. The vehicle deviated grossly from the
     planned trajectory in azimuth and velocity, and executed abnormal maneuvers in
     pitch and yaw. The missile was destroyed by the RSO at 293.5 seconds, some 12
     seconds after SECO.
141. 87D (Peg Board II), 9 Aug 62, Response Mode 4, Flight Phase 2.5: Failure of the
     sustainer/vernier hydraulic system to maintain system pressure prevented
     normal operation during the vernier solo phase.
142. 57F (Crash Truck), 10 Aug 62, Response Mode 5, Flight Phase 1: The roll program
     failed. The missile was destroyed by the RSO at 68 seconds.
144. 179D (Mariner R-2), 27 Aug 62, Response Mode NA, Flight Phase 2: Flight was
     successful although roll control was lost during the period from 140 seconds to
     190 seconds due to erratic performance of vernier engine #2. Before and after this
     time interval, vernier #2 and all other Atlas and Agena systems performed
     normally.·

146. 4D (Briar Street), 2 Oct 62, Response Mode 4, Flight Phase 2: The missile self-
     destructed at 183 seconds. The vernier engines shut down prematurely at 46
     seconds. Subsequently, closure of the vernier bleed valves led to excessively high
     sustainer performance and premature shutdown at 181.3 seconds.
148. 215 D (Ranger-5), 18 Oct 62, Response Mode NA, Flight Phase 5: Flight was
     regarded as successful although failure in the ground control system 35 minutes
     after launch prevented accomplishment of primary lunar impact and study
     m1ss10n. The guidance .rate beacon failed at 94.6 seconds but backup
     differentiated tracking data kept the vehicle within normal limits.
153. 13F (Action Time), 14 Nov 62, Response Mode 4, Flight Phase 1: The flight was
     terminated when sustainer and vernier engines shut down prematurely at


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