RON DUPAS COLLECTION
No. 5415. Fairchild 92 XNQ-1 (75726) US Navy
Photographed ca. 1947, courtesy The Fairchild Corporation

Fairchild 92 XNQ-1

10/31/2013. Remarks by Johan Visschedijk: "This aircraft was produced as the XNQ-1 for the USN. The first of two prototypes, BuNo 75725 and 75726, was first flown by Richard Henson at Hagerstown, Maryland on October 7, 1946. In 1947 both prototypes were delivered to the USN at Patuxent, where they were evaluated by a team led by Commander Robert M. Soule. Eventually they were rejected, one of the issues was exhaust gasses entering the cockpit due to a sealing problem.

The first prototype was subsequently used as an engine test bed, its Lycoming R-680-13 radial being replaced by a Lycoming GSO-580 horizontally-opposed eight-cylinder. It was lost in an accident in1950.

The second aircraft, fitted with a larger stabilizer, was evaluated by the USAF as a primary trainer in 1949, designated T-31, others evaluated were the Beech 45 T-34 and the Temco TE-1A. On March 24, 1949, after only three weeks of trials at Wright Field, Dayton, Ohio, the T-31 was selected. Fairchild would produce 100 aircraft as the Model 129, however, due to budget restrictions the order was cancelled later in 1949.

Subsequently BuNo 75726 came on the civil register as N5756 and was operated for ten years by the Civil Air Patrol in Washington, D.C., whereafter it it was acquired by a private owner. In the mid-1970s the aircraft was offered to the Antique Airplane Association of Blakesburg, Iowa. On April 15, 1983, the aircraft was registered to Dominick D. 'Don' Pellegreno of Rhome, Texas, who restored the aircraft, and it was flown again on May 20, 1992. It is still on the register as of this day."

The following data relate to the XNQ-1.

Type: Two-seat Primary-Basic Trainer.
Wings: Low-wing cantilever monoplane. All-metal structure with stressed metal skin. Trailing edge flaps between ailerons and root joints. Flaps all-metal including covering, ailerons metal-framed and fabric covered.
Fuselage: All-metal structure.
Tail unit: Cantilever monoplane type. All-metal tail plane and fin, metal-framed fabric covered elevators and rudder. Trim-tab in movable surfaces.
Landing gear: Retractable type. Main wheels raised inwardly into pockets in leading edge of wing roots. Electrical retraction. Non-retracting castoring and steerable tail wheel.
Power plant: One Lycoming R-680-13 nine-cylinder radial air-cooled engine with normal rating of 280 hp and with 295 hp available for take off. Hamilton Standard two-blade constant-speed airscrew. Fuel capacity 80 gal (302 l).
Accommodation: Crew of two in tandem beneath a one-piece sliding "bubble" canopy. Dual controls. Air Force-Navy standardized functional safety cockpit layout.

Created June 15, 2006