On June 26, 2003, at 1924 Pacific daylight time, an experimental McAnally Glasair JM-1, N104JM, lost engine power during takeoff, collided with obstacles during a forced landing attempt, and came to rest inverted near Hollister Municipal Airport (307), Hollister, California. The owner was operating the airplane under the provisions of 14 CFR Part 91. The two occupants, both certificated pilots, sustained serious injuries; the airplane sustained substantial damage. The personal local flight departed Hollister Municipal Airport about 1920. Day visual meteorological conditions prevailed, and no flight plan had been filed. The primary wreckage was at 36 degrees 53.36 minutes north latitude and 121 degrees 24.36 minutes west longitude. In a written statement, the owner/pilot reported that the airplane had just departed runway 24 when the engine started to surge. He then reduced power and leaned the mixture in an attempt to smooth it out. Following a turn back towards the airport, the airplane was parallel to runway 31 at 800 feet when the engine quit. Instead of trying to land on a busy road, the pilot chose instead to head for a stubble field. During the descent, the airplane clipped a tree, and then struck a piece of concrete before coming to rest inverted. The electric fuel boost pump, which according to the pilot was required for flight, was not turned on. The pilot did not report any mechanical malfunction with the airplane. To prevent similar accidents in the future, he recommended turning the electric fuel pump to the "ON" position, prior to departure. The pilot reported that the ambient temperature was 38 degrees Celsius. The National Transportation Safety Board investigator-in-charge (IIC) and a representative from Textron Lycoming, a party to the investigation, examined the engine. They manually rotated the engine, and obtained thumb compression on all four cylinders in firing order. They observed normal lift action on each rocker assembly; the rocker housing contained oil. They removed the top spark plugs. The electrodes were circular and their coloration was consistent with normal operation according to the Champion Spark Plug Check-A-Plug chart AV-27. A borescope inspection revealed no mechanical deformation on the valves, cylinder walls, internal cylinder heads, or pistons. The engine driven fuel pump's rubber diaphragm was unbroken and the diaphragm pump shaft gasket was in place. The plunger in the fuel distribution valve moved freely and investigators observed no contamination. The fuel selector valve was in the auxiliary position with the other positions labeled as off and main. Fuel lines went from each main and auxiliary tank to the fuel selector valve. A line then went from the fuel selector valve to the electric boost pump, to the gascolator, to the engine driven fuel pump, and finally to the fuel servo. The investigators were unable to test the experimental electric ignition system installed on the engine. They noted no other discrepancies with the engine. The IIC contacted a representative from the New Glasair, LLC, regarding vapor lock situations in the Glasair airplane. The representative advised the IIC that the company recommends to the builder to provide cooling air to the fuel system components. Also, the builder should recognize the increased potential for vapor lock during higher ambient temperatures. On the newer model of airplanes, the company provides a circular cooling shroud for the mechanical fuel pump. The installation of a cooling shroud on older airplanes is optional. The accident airplane had cooling shrouds installed for the engine driven fuel pump and the firewall mounted electric boost pump. Item number 5 on the pretakeoff portion of the checklist notes to turn on the electric boost pump.