22.   7C, 18 Mar 59, Response Mode 4, Flight Phase 1: Booster engines shut down
      prematurely at 129.4 seconds, but booster section was not jettisoned until the near-
      normal time of 153 seconds. Guidance was inoperative. Since the sustainer
      engine could not gimbal before booster separation, the autopilot was unable to
      stabilize the missile after BECO. The sustainer shut down about 40 seconds before
      propellant depletion. The reentry vehicle spin rockets fired prematurely at 86.3
      seconds after liftoff.

23.   3D, 14 Apr 59, Response Mode 4, Flight Phase 1: Performance of B2 engine
      dropped 36% at launch, resulting in a violent pitch as missile left the launcher.
      Flight control system corrected missile attitude, and flight continued at reduced
      thrust until a more violent explosion tore the thrust section away from the missile
      at 26.1 seconds. The sustainer continued operating with decreased thrust until
      shutdown by the safety officer at 36 seconds. Debris impacted about 3000 feet
      from launch point.
24.   7D, 18 May 59, Response Mode 4, Flight Phase 1: Failure in pneumatic system
      resulted in missile explosion at 65 seconds. A temporary failure of the thrust-
      structure fairing at liftoff strained the pneumatic lines and disconnects, resulting
      in leaks in the pneumatic system.
25.   5D, 6 June 59, Response Mode 4, Flight Phase 2: Either structural damage at
      booster staging or failure of the booster staging valve to dose resulted in a fuel
      leak and explosion at 159.3 seconds. Impact occurred near the flight line about
      780 miles downrange.
30.   10D (Mercury), 9 Sep 59, Response Mode 4, Flight Phase 2: Booster section failed
      to jettison resulting in a final velocity about 3000 ft/sec low and an impact range
      about 500 miles short of target.
32.   17D, 16 Sep. 59, Response Mode 4, Flight Phase 2.5: :Flight was considered a
      success since impact was within two miles of target point. However, failure of the
      vernier hydraulic package resulted in loss of missile control during the vernier
      solo phase.
35.   26D, 29 Oct 59, Response Mode 4, Flight Phase 2.5: Vernier solo phase was
      unstable in pitch·due to loss of thrust from V2 vernier engine. The V2 engine lost
      chamber pressure during booster jettison. Impact was about 14 miles short and
      out of splash net.
36.   28D, 4 Nov 59, Response Mode NA, Flight Phase 2: The flight was normal, but
      was terminated prematurely when the range-safety impact-predictor system
      failed.
37.   15D, 24 Nov 59, Response Mode NA, Flight Phase 2.5: Flight was normal, except
      the reentry vehicle failed to arm or separate.


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