38.   20D (Able M, 26 Nov 59, Response Mode 4, Flight Phase 1: Third and fourth
      stages and payload broke off about 47 seconds. Atlas flight was normal and
      second stage ignited properly after Atlas SECO.
43.   6D (Dual Exhaust), 26 Jan 60, Response Mode 4, Flight Phase .2 and 2.5: At 175
      seconds, as a result of a full-scale positive yaw command generated for five
      seconds, the missile stabilized on an erroneous heading. When a range-rate flag
      was lost 20 seconds later, the differentiated range-rate data substituted for
      measured data corrected the erroneous azimuth by generating a full-scale
      negative yaw command. The substituted data resulted in slightly erratic steering
      and a premature VECO signal that was not acted upon The verniers were
      subsequently cutoff by the backup signal.

45.   29D (Midas I), 26 Feb 60, Response Mode 4, Flight Phase 2.5: Flight was normal·
      until firing of the retro rockets after Atlas separation. An explosion at this time,
      probably due to activation of the Agena inadvertent separation destruct system,
      destroyed both the Atlas vehicle and the Agena.

46.   42D, 8 Mar 60, Response Mode 4, Flight Phase 2.5: Flight was considered a
      success although failure of the vernier hydraulic system resulted in loss of attitude
      control during the vernier solo phase.
47.   51 D, 10 Mar 60, Response Mode 1, Flight Phase 1: Due to combustion instability,
      an explosion occurred in the Bl chamber before missile movement. Missile was
      destroyed at 2.5 seconds after 2-inch motion when main propellants ignited.
48.   48D, 7 Apr 60, Response Mode 1, Flight Phase 1: Missile was destroyed in launch
      stand during launch attempt, apparently due to combustion instability in the B2
      thrust chamber.
50.   23D (Lucky Dragon), 6 May 60, Response Mode 3, Flight Phase 1: An inoperative
      pitch gyro caused pitch instability, and resulted in destruct at 25.6 seconds.
54.   62D, 22 June 60, Response Mode 4, Flight Phase 2.5: Vernier engines were cutoff
      by autopilot backup when guidance discrete was not sent. Impact was 18 miles
      long.
56.   60D, 2 July 60, Response Mode 4, Flight Phase 2: Depletion of helium bottle
      pressure led to low sustainer and vernier engine thrust, and eventually early
      shutdown of engines. Impact was 40 miles short of target.
57.   74D (Tiger Skin), 22 July 60, Response Mode 5, Flight Phase 1: A pitchover rate
      that was 69% above the nominal rate resulted in vehicle breakup at 69.2 seconds.




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