STANDARD 3: DELIVERY ACCURACY. The LV system will be capable of providing orbital parameter accuracies within the 3 sigma values specified in Table 1, Orbital Parameter Accuracies, of the LCCV SPD. This standard is met if: (Template No. 10)

a) The orbital parameter accuracies at the final orbit injection point for each payload mission are within the 3 sigma values specified in Table 1 of the LCCV SPD.

b) During park orbit or transfer orbit coasts, the LV is capable of orienting the upper stage/payload to any desired attitude and holding attitude to within 6o (3 sigma).

c) During park orbit or transfer orbit coasts, the LV is capable of providing a commanded roll rate, in either direction, of up to 2.0 degrees per second.

d) Prior to separation, the LV is capable of pointing the upper stage/payload to any desired attitude and either minimizing all rotation rates (3-axis stabilized missions) or providing a spin about the longitudinal axis (spin-stabilized missions) with attitude errors, rotation rates, spin rates, and spin axis orientation accuracies as specified in paragraph 3.2.1.4.3 of the LCCV SPD.

STANDARD 4: SCHEDULE DEPENDABILITY. The LV system (ground and launch vehicle segments) shall provide the highest practical probability of launching within

-3 to +10 calendar days of the scheduled launch time. Attributable delays include EELV equipment, processing, and weather related delays. This standard is met if:

a) The Offeror defines the probability of launching within the -3 to +10 day window. (Template No. 12)

b) The Offeror has used an appropriate analysis or simulation methodology, with justifiable inputs, in establishing the probability of on-time launch. The methodology takes into consideration outside influences such as weather conditions, daylight restrictions and electromagnetic radiation, and component/equipment failures during launch processing.

STANDARD 5: LAUNCH RATE CAPACITY AND RESILIENCE. The EELV system has the flexibility to efficiently operate over a range of potential processing rates and provides the basic launch rate capacity to support the Government portion of the NMM requirements. This standard is met if:

a) The system has sufficient throughput to support the range of Government requirements as specified in the Government portion of the NMM (LCCV SPD Tables 1a and 2a), and provides additional launch rate capacity for resilience. (Template No. 11)

b) The launch rates are achievable taking into account weather delays, launch range conflicts with other spacelift systems, and other typical launch delays such as processing task

timeline variations, ground support system downtimes, and unscheduled vehicle maintenance activities.

c) The Offeror's maintainability and maintenance concepts emphasize rapid fault detection and isolation, and are commensurate with launch rate and schedule dependability requirements.

STANDARD 6: LAUNCH RESPONSIVENESS. To ensure scheduled launch timeliness and to accommodate unplanned launches, the LV shall be capable of rapidly and repeatedly responding to requests for launches. This standard is met if:

a) The LV system is capable of supporting an unscheduled DoD launch in less time than the current processing timelines of 45 days for MLV and 180 for HLV. (Template No. 12)

b) The response capability is based on a timeline analysis which includes processing the vehicle, mating the launch vehicle with the payload, and final processing for launch. (Template No. 12)

STANDARD 7: CRISIS REPLENISHMENT (SURGE). The EELV system shall include a capability to surge above the scheduled number of missions in the NMM. This standard is met if the Offeror defines and substantiates the number of extra missions and the associated time to launch these missions in response to a crisis situation. (Template No. 12)

STANDARD 8: PAYLOAD FLIGHT ENVIRONMENT. The EELV system provides a suitable flight environment for the Government payloads of the NMM. This standard is met if:

a) The acoustic environment within the fairing is commensurate with the levels acceptable by the Government payloads of the NMM, as delineated in LCCV SPD paragraph 3.2.3.3.3, Pyro Shock.

b) The maximum shock spectrum at the payload interface is compatible with the levels acceptable by the Government payloads of the NMM, as delineated in LCCV SPD paragraph 3.2.3.3.3, Pyro Shock.

2.6.2.2 Factor 2: Reliability

STANDARD: VEHICLE Design Reliability. The Offeror's concept meets LCCV SPD vehicle design reliability requirements. This standard is met if:

a) Design reliability for each LV, including hardware, software, and firmware, from launch commit through CCAM is at least 0.98 (at a 50% confidence level) for the LV. (Template No. 14)