the x and z velocity channels. As a result, the missile impacted about 12 miles short and 0.2 miles right of target. 170. 52F (Tall Tree 4), 23 Mar 63, Response Mode 4, Flight Phase 1: Missile self- destructed at about 91 seconds for unknown reasons. Impact was near the flight line about 120 miles downrange. 171. 65E (Black Buck), 24 Apr 63, Response Mode NA, Flight Phase 2.5: Vernier hydraulic-system pressure was lost at 301 seconds, resulting in loss of vernier- engine control during the vernier solo phase. The reentry vehicle impact point was not perceptibly affected by this malfunction. 176. 139D LV-3A/ Agena B (Big Four), 12 Jun 63: Response Mode 4T, Flight Phase 1: Flight appeared normal until about 88.4 seconds when, due to a hydraulic failure, the vehicle made a violent right and down maneuver. The missile broke up five seconds later at 93.4 seconds. 181. 24E (Silver Doll), 26 July 63, Response Mode 4, Flight Phase 2: Spurious voltage transients caused premature pressurization of the vernier solo tanks at 101.3 seconds, and premature sustainer engine shut down just after booster separation at 141 seconds. 187. 63D (Cool Water III), 6 Sep 63, Response Mode 4, Flight Phase 1: All systems performed satisfactorily till 110 seconds, when the sustainer/vernier hydraulic pressure dropped from 3080 to 490 psig. The failure resulted in premature shutdown of the sustainer engine at 136 seconds. Booster-engine cutoff occurred normally at 140.3 seconds, and the booster was successfully jettisoned. The impact point occurred about 620.miles downrange. 188. 84D (Cool Water IV), 11 Sep 63, Response Mode 4T, Flight Phase 2~5: Flight seemed normal through SECO, although the pneumatic precharge to the vernier solo accumulator was lost at 96.6 seconds. Due to this failure, missile stability was lost near the start of the vernier solo phase. The R/V probably failed to separate. 189. 71E (Filter Tip), 25 Sep 63, Response Mode 4T, Flight Phase 2: Visual observers reported a boat-tail fire, radical oscillations in yaw, and rough running booster and sustainer engines. Failure of the sustainer hydraulic system during the staging sequence resulted in loss of missile stability at 140 seconds. Sustainer and vernier engines shut down at about 267 seconds with the impact point about 600 miles downrange. 190. 45F (Hot Rum), 3 Oct 63, Response Mode 1, Flight Phase 1: The B-1 booster-engine fuel valve failed to open during the start sequence, so the engine did not ignite. Missile toppled over and exploded. 9/10/96 125 RTI
Vision Description (EN)
Page 125 continues a list of missile and launch vehicle test incidents (entries 169–190), with each entry documenting a test designation, date in 1963, response mode, flight phase, and failure mechanism. The text is entirely unformatted with no images, diagrams, tables, or signatures. Failure modes documented include hydraulic system losses, engine malfunctions, fuel valve failures, and structural breakup. The footer displays the document date 9/10/96, page number 125, and the marking RTI. Entry 169 is a continuation from the previous page. Text is clear and fully readable.
Descrição Vision (PT-BR)
A página 125 continua uma lista de incidentes em testes de mísseis e veículos de lançamento (entradas 169–190), com cada entrada documentando uma designação de teste, data em 1963, modo de resposta, fase de voo e mecanismo de falha. O texto é inteiramente sem formatação, sem imagens, diagramas, tabelas ou assinaturas. Os modos de falha documentados incluem perdas de sistema hidráulico, mau funcionamento de motores, falha de válvula de combustível e ruptura estrutural. O rodapé exibe a data do documento 9/10/96, número da página 125 e a marcação RTI. A entrada 169 é uma continuação da página anterior. O texto é claro e totalmente legível.