Prototype XP6M-1 made its first flight on July 14th, 1955 and resulting data collected forced changes to the engine placement. This prototype was then lost on December 7th, 1955, when the aircraft disintegrated mid-flight with the loss of all four crew aboard due to a failure in the tail unit. The second prototype then followed in a first flight recorded on May 18th, 1956. It too, however, suffered a catastrophic failure in the tail unit. In this case, all four crew exited the aircraft safely.
Undeterred, the USN SeaMaster program continued and resulted in the YP6M-1 pre-production model of 1957. The example began its testing phase the following year which ultimately revealed several major shortcomings of the design as a whole. The aircraft was of a heavy configuration and this was coupled to poor controls and underpowered engines unsuitable for on-water/over-water operation. Five additional airframes were ordered and changes instituted for the better: the Allison engines were given up in favor of 4 x Pratt & Whitney J75 turbojets which promised more power and vision out-of-the-cockpit was improved as was the avionics suite. An in-flight refueling probe was added to help increase the operational reach of the aircraft.
This revised design emerged as the "P6M-2" and eight total airframes followed. By this time, however, the bloated and oft-delayed program has met its end - cancelled before operational service was reached. The USN elected to fund its ballistic missile submarine program instead and all remaining SeaMaster airframes were scrapped and lost to naval aviation history.
As completed, P6M-2 featured an overall length of 134 feet, a wingspan of 103 feet and a height of 32 feet, 5 inches. Its operating crew was four including two pilots. Primary armament was a 4,000lb bomb load while point-defense was handled by a 2 x 20mm cannon arrangement in a tail turret. The aircraft weighed 91,300lbs when empty and showcased a Maximum Take-Off Weight (MTOW) of 176,400lbs. Power from the finalized 4 x Pratt & Whitney J75-P-2 turbojets outputted at 17,500lbs thrust each and allowed for a maximum speed of 630 miles per hour, a range out to 2,000 miles and a service ceiling up to 40,000 feet.
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