The technical objectives of A-DECK are: 1)Flight Weight including rideshare payloads will be less than 500 Kg. 2)First fundamental frequency of integrated A-DECK System including ESPA or Type C Adapter, payload(s), avionics and release mechanisms will be greater than 50 Hz. 3)After initial qualification, A-DECK must not require additional EELV mission unique design or analysis. 4)A-DECK delivery ICD and Verification products must be sufficient for acceptance of integrated A-DECK as ready to fly meeting launch vehicle, range safety and customer operations requirements. 5)A-DECK mechanical interface to launch vehicle must be through multi-point pinned attachments to the interior of an ESPA or a Type C Adapter. 6)Type C Adapter will utilize standard EELV 62.01" (1575 mm) bolt hole template for both forward and aft interfaces. 7)A-DECK electrical interface to launch vehicle will be through a single shielded multi-line cable to the launch vehicle secondary or designated electrical panel. 8)A-DECK avionics must control, monitor and support all A-DECK mounted spacecraft and/or hosted technical payloads in manner not to interfere with launch vehicle operations or primary spacecraft. 9)A-DECK integration, check out and acceptance will be performed at facilities outside of the Primary Spacecraft integration and check out facility. 10)A-DECK and the A-DECK payloads must remain electrically and mechanically dormant until the launch vehicle transmits its initiate signal to the A-DECK avionics. 11)To the greatest extent possible A-DECK will incorporate existing mechanisms, avionics and components designed to support Small Satellites as an example the Poly Pico-satellite Orbital Deployer (P-POD).