One of the main purposes of this program was the development of a better igniter. The igniter tested was attached to the head end of the propellant grain and coated with a pyrotechnic. Based on three tests it appeared that the delayed ignition problem had been resolved. Thereafter, several other tests were run until the igniter was adjudged to be reliable.

Measures to be taken for hydrogen-peroxide fuel economy for the Mercury spacecraft attitude control system were studied at a coordination meeting. Items considered were orbital attitude, retroattitude hold sequence, and salvo versus ripple retrorocket firing. Astronaut Virgil Grissom reported that the salvo method had already been proven to be unsatisfactory on the Mercury procedures trainer.

Based on a request from the Manned Spacecraft Center, McDonnell submitted a review of clearances between the Mercury spacecraft 15B retropack and the launch vehicle adapter during separation maneuvers. This review was prompted by the fact that additional batteries and a water tank had been installed on the sides of the retropack. According to the McDonnell study the clearance safety margin was quite adequate.