9.    3B, 19 July 58, Response Mode 4T, Flight Phase 1: Random failure of yaw rate
      gyro caused violent maneuvers resulting in rupture of LO2 tank, engine
      shutdown, and a fire near the lube oil drain. Missile broke up about 42 seconds
      with impact about 2 miles downrange and 0.4 miles crossrange left.
11.   SB, 28 Aug 58, Response Mode 4, Flight Phase 2.5: Missile was normal to SECO.
      After SECO, failure of hydraulic system caused loss of vernier engine control.
      Warhead impacted close to intended target.

12.   BB, 14 Sep 58, Response Mode 4, Flight Phase 2.5: Warhead impacted close to
      target although control was lost after SECO due to failure of vernier-engine
      hydraulic system.

13.   6B, 18 Sep 58, Response Mode 4, Flight Phase 1: Except for a late-opening
      sustainer fuel valve, flight was apparently normal until 80.8 seconds, when the Bl .
      turbopump failed. Performance of the Bl engine and the axial acceleration
      dropped sharply at about 81.7 seconds, and the B2 system shut down about 0.1
      seconds later. The sustainer and vernier engines continued to operate normally
      until .82.9 seconds, when the missile exploded. Impact was about 25 miles
      downrange and about 0.6 miles right of the flight line.            •
14.   9B, 17 Nov 58, Response Mode 4, Flight Phase 2: The flight was terminated at
      227.6 seconds by premature fuel depletion caused either by failure of the
      propulsion utilization system or by a tanking error. Missile impacted near the
      flight line about 2300 miles downrange, some 850 miles short of target.
18.   13B, 15 Jan 59, Response Mode 5, Flight Phase 1: The vehicle appeared normal for
      the first 50-60 seconds, at which time it was obscured by clouds. It was probably
      normal until about 100 seconds, but prelaunch removal of the mainframe
      telemetry system prevented a precise determination. Beginning about 101
      seconds, various erratic pitch, yaw; and roll rates and oscillations were noted with
      accompanying drops in acceleration and velocity. These rates become excessive at
      106.6 seconds. At 121 seconds, the nosecone telemetry system showed that yaw
      and pitch rates abruptly increased, and this condition existed ·until reentry at 281
      seconds. All thrusting apparently stopped between 121 and 123 seconds. The
      missile impacted about 170 miles downrange and 7.5 miles left.
19.   4C, 27 Jan 59, Response Mode 5, Flight Phase 2: Since the guidance system was
      inoperative throughout, the flight path was controlled by the pre-programmed
      flight control system. Impact was about 80 miles long and 30 miles left of target
      point.
21.   SC, 20 Feb 59, Response Mode 4, Flight Phase 2: After a normal booster phase,
      missile exploded at 173 seconds (BECO at 149.2 sec) apparently due to loss of fuel-
      tank pressure and subsequent rupture of LOX/ fuel-tank bulkhead. Impact was
      about 1000 miles downrange and 6 miles left.

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