94.   26E, 8 Sep 61, Response Mode 4, Flight Phase 2: Sustainer engine shut down
      prematurely during the booster jettison sequence. Most probable cause was drop
      in fuel flow to the gas generator. The vernier engines continued to burn for about
      28 seconds after the sustainer shut down. Vernier thrust decayed at 137 seconds,
      guidance platform tumbled at 163 seconds. The missile remained intact until at
      least 470 seconds, when data were lost. Impact was about 525 miles downrange.
95.   106D (LV-3A)/ Agena B (First Motion), 9 Sep 61, Response Mode 1, Flight Phase 1:
      Failure of an umbilical to eject allowed a commit/stop-power signal to reach the
      missile. Lack of electrical power 0.265 seconds after liftoff caused the vehicle to
      fall back on the launch
                         .
                              pad after
                                    .
                                        a rise of about 18 inches.

99.   105D (LV-3A)/ Agena B (Big Town), Midas IV, 21 Oct 61, Response Mode NA,
      Flight Phase 2: Flight was regarded as a success, since the Agena compensated for
      Atlas anomalies. Atlas roll control was lost at 186 seconds, resulting in a roll rate
      of over 40° per second at Agena separation. Control in pitch and yaw was
      maintained. A LOX leak affected sustiliner performance just before SECO and
      throughout the vernier phase.
100. 32E, 10 Nov 61, Response Mode 4T, Flight Phase 1: Sustainer engine shut down
     0.7 seconds after liftoff. Although a fire appeared in the thrust section at 19
     seconds, booster engines maintained stability until 24.5 seconds, when the B2
     engine-performance began to decay. All control was lost after this point, and the
     missile was destroyed by the RSO at 35 seconds. Impact was about 2500 feet
     downrange and 320 feet crossrange.
101. 1170 (Ranger-2),18 Nov 61, Response Mode NA, Flight Phase 4: The Atlas booster
     functioned normally. A parking orbit was attained during the Agena first burn
     although roll control was not maintained due to failure of the roll gyro. When
     control gas was depleted, missile lost stability and began to tumble. Second
     Agena bum lasted only one second.
103. 108D (LV-3A)/Agena B (Round Trip), 22 Nov 61, Response Mode 4T, Flight
     Phase 2: Flight was not successful since vehicle failed to achieve orbit. Loss of
     pitch control at 244 seconds was attributed to aerodynamic heating. At Agena
     separation the Atlas had pitched up 145°.
108. SF,12 Dec 61, Response Mode 5, Flight Phase 2: A failure in the inertial guidance
     system of 1.06 seconds duration caused the existing inertial X velocity to be
     inserted in the Z-velocity channel. As a result, the missile impacted 575 miles
     short and 30 miles left of target.
110. 6F, 20 Dec 61, Response Mode 4T, Flight Phase 2: Flight appeared normal until
     staging. During booster jettison, sustainer and vernier hydraulic pressure began
     to decay, leading to compete loss of sustainer yaw and pitch control at 229 and
     232 seconds, respectively. Missile began tumbling at about 226 seconds.

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