Continued
	To investigate if any takeoff limitations existed due to the increased forward center of gravity-high gross weight combinations of the later model aircraft configuration, a test plan was developed to conduct tests first with the prototype C-130 ski equipped aircraft (55-021)-again at Bemidji, Minnesota. The second phase of the ski tests were conducted under actual on-site snow-ice conditions in the Antarctic utilizing the first Navy production aircraft (Air Force tail number 59-5922), which was available at the Lockheed factory during September 1960. Note: The aircraft, Lockheed's number 3562, carried Bureau of Naval Operations number 148318. Because Bemidji was at a lower elevation than the 9,000 ft. Antarctic operational site, the higher elevation was simulated by using reduced power during the takeoff tests. Along with developing center-of-gravity (e.g.)-gross weight envelope limits, other parameters to be determined included takeoff distances, rotation speeds, lift-off speeds, and aircraft handling characteristics. The data was incorporated in the C-130D flight manual to augment the ski test data previously obtained in 1957 and 1958. The e.g. and gross weight limits would be used on the Navy C-130BL aircraft until those aircraft could actually be tested in the Antarctic and data evaluated. A total of 37 takeoff runs were made (three were aborted) and 15 hours and 10 minutes of flight time was recorded at Bemidji between January 22 and March 3, 1960. Due to relatively mild weather during the tests no deep or rough snow conditions existed which limited the program. However, the following conclusions were reached:
	a.	The results of the program were obtained on relatively ideal snow conditions. Deep, wet, and rough snow would further reduce the aircrafts performance.
	b.	The forward e.g. limits for the C-130D (operating on wheels) were too far forward for ski operation when attempting takeoffs at high altitude runways where power would be reduced.
	c.	The aircraft, operating at reduced power, would not take off within a 10,000 ft. run with a e.g. near the forward limit at gross weights of 105,000 lbs. or greater.
	d.	The use of RATO would supply sufficient power for takeoff with an e.g. near the forward limit and gross weights of 105,000 or greater
	Three takeoffs had to be aborted after running in excess of 10,000 ft. on 3 to 5 inches of packed granular snow and the aircraft's airspeed would not accelerate above 70-76 knots. It was apparent that there was a definite area that needed to be tested extensively on the C-130BL aircraft, i.e., high gross weight (120,000 lbs. or greater), and forward e.g. takeoffs from high altitude runways. It was also apparent that a difficult problem existed and extreme caution would have to be taken during testing for those particular conditions. During the summer of 1960, the Navy prepositioned spare parts to support the three C-130BLs to be used by U.S. Navy Air Development Squadron Six (VX-6) to airlift supplies for Project "Deep Freeze" and the "Slide III" test aircraft. Assistance to the test team was to be rendered by VX-6 in the form of maintenance capability (personnel and facilities) during the testing.
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