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3. KSC Landing Runway - The KSC runway geometry is 15 000 feet in length and 300 feet in width. The KSC runway geometry complies with JSC-07700, volume X, "Space Shuttle and Ground System Specifications Requirements;" i.e., 12 500 feet in length and 150 feet in width. Tire blowout due to runway groove configuration and surface texture is controlled by stringent criteria for inspection and replacement of tires. Criteria are defined in Space Shuttle and maintenance requirements and in Specification Document V51, File III, Landing Gear Susbystem. 

4. Landing at KSC with Present Tires, Brakes, and Nosewheel Steering - Tire spinup wear is controlled by Orbiter downweight, touchdown velocity, and runway roughness. Tire blowout is minimized by end-of-mission weight (limited to 211 000 pounds by JSC-07700, volume X), inspection and replacement of tires, design to reduce brake failure/wheel lockup probability, weather constraints (crosswinds or tailwind), and brake-on time, velocity, and pressure. 

Loss of vehicle directional control is minimized by differential braking in combination with nosewheel steering, crosswind/tailwind limitations, runway coefficient of friction, and a nosewheel steering disengage to prevent nosewheel steering hardover. 

XX. TAL ABORT

TAL abort is an automated intact abort mode provided by the STS program to cover a single Space Shuttle main engine (SSME) failure plus one other non-SSME failure and still safely recover the Orbiter and flight crew. The period of exposure covers the time from last capability to support an RTLS abort and the first capability to perform an AOA to a continental United States landing site (EAFB, WSMR, or KSC). The exposure time interval is a function of the launch azimuth (orbit inclination), proximity of TAL landing site, cargo weight, and trajectory design. TAL sites and appropriate flight software provide a targeted landing capability for any system or multiple SSME failures during a portion of the ascent trajectory whether a "single engine out" TAL exposure exists or not. 

The weather-related Flight Rules plus criteria for runway availability are covered in the KSC landing considerations topic. The major differences for TAL are: 

1. Brake energy is assumed to be 55 MFP at 10 ft/secĀ² versus 42 MFP at -7.5 ft/secĀ² for end of mission (EOM).

2. Crosswind is limited to 15 knots versus 10 knots at EOM. 

3. Visibility with full landing aids may be reduced to <5 statute miles if landing aids available vs <7 nautical miles at EOM. 

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