200. IIIC-19, 6 Nov 70, Vehicle 19, Response Mode NA, Flight Phase 3.5 and 5: All
     booster systems performed essentially as planned. Transtage experienced a
     guidance anomaly during coast prior to second bum resulting in an improper
     orbit.

212. IIIB/ Agena D (AFSC), 16 Feb 72, Response Mode 4, Flight Phase 3: After an
     apparently normal Titan III B boost phase, the Agena failed to- ignite. The
     payload impacted about 1500 miles downrange.

232. Titan IIIE, #El, 11 Feb 74, Response Mode 4, Flight Phase 3: All Titan booster
     functions and Centaur separation were properly performed~ Centaur stage failed
     to ignite.

244. TIIIC-25, 20 May 75, Vehicle 25, Response Mode NA, Flight Phase 2.5: All systems
     performed satisfactorily through Stage 11/111 separation. About 230 milliseconds
     after staging discrete was issued, the IMU power supply failed. Transtage then
     tumbled and the first transtage bum failed to occur leaving transtage and attached·
     payload in the parking orbit.
252. TIIIC-29, 14 Dec 75, Vehicle 29, Response Mode NA, Flight Phase 5: All launch
     vehicle objectives were met. However, satellite propulsion system malfunctioned
     putting satellite in uncontrollable position with no possibility of restoring mission
     capability.
261. 111B/Agena D (AFSC), 15 Sep 76, Response Mode 4, Flight Phase 2: The stage-2
     engine failed to respond to shutdown commands and thus burned to propellant
     depletion. Cause was thought to be a hard contaminant that blocked the fuel
     valve.
268. 23E-6/Centaur D-lT, 5 Sep 77, Response Mode NA, Flight Phase 2: Flight was
     regarded as a success, although the second-stage velocity was low, probably due
     to a detached line diffuser lodged on top of the prevalve.
272. TIIIC-17, 25 Mar 78, Vehicle 35, Response Mode 4T, Flight Phase 2: Vehicle
     performance was satisfactory until 16.4 seconds beyond Stage-2 start. At this time
     the Stage-2 hydraulic system began and continued over-pressurizing until the
     system burst after 125 seconds of Stage-2 operation. The pressure then dropped to .
     zero, the vehicle tumbled out of control, and guidance shut down the second stage
     after detecting negative acceleration. The RSO sent arm at 629 seconds and
     destruct at 630 seconds.
306. 34D (AFSC), 28 Aug 85, Response Mode 4T, Flight Phase 1: The first-stage engine
     suffered three separate major anomalies: (1) during subassembly-2 (S/ A-2) start
     transient (110 sec), a large oxidizer leak of 165 lb/sec occurred in the oxidizer
     suction line; (2) at 213 seconds, an internal fuel leak of 30 lb/sec occurred in S/ A-1
     downstream of the combustion chamber and created a vehicle side force; (3) the


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