Breguet 462
WINGS. Low-wing cantilever monoplane. Wing in three sections, a centre-section of parallel chord and thickness, and two outer-sections tapering in chord and thickness from the roots to the elliptic tips. Structure consisted of two steel "I"-section spars braced together to form a girder, and a number of three-piece light alloy (L.2R) former-ribs fixed to the spars by gusset-plates and rivets. Leading-edge covered with light alloy sheet (L.2R). Upper surface of wing covered with light alloy strips running at right angles to spars, lower surface between the two spars covered with fabric. Entire straight trailing-edge provided with slotted flaps, in four sections for each half-wing. The inner pairs acted as camber-changing flaps and the outer as ailerons.
FUSELAGE. Metal structure in two sections, rectangular forward and oval aft. Structure built up of a number
ween the two spars covered with fabric. Entire straight trailing-edge provided with slotted flaps, in four sections for each half-wing. The inner pairs acted as camber-changing flaps and the outer as ailerons.
FUSELAGE. Metal structure in two sections, rectangular forward and oval aft. Structure built up of a number of cross-frames, interconnected by stringers and covered with stressed sheet riveted on in longitudinal panels. The whole fuselage was of light alloy (L.2R).
TAIL UNIT. Monoplane type with fins and rudders at the extremities of the tail-plane. Steel spars and light alloy ribs. Tail-plane and fin covered with light alloy sheet, rudder and elevators with fabric. Trimming-tabs in rudder and elevators.
UNDERCARRIAGE. Retractable type. In two separate units, each unit consisted of a fork carrying an "Electron" wheel and backwardly inclined struts, which did break inwardly to raise the wheel until it was buried almost entirely within the engine nacelles. Hydraulic retraction. Wheels had balloon tires and brakes. Steerable tail-wheel.
POWER PLANT. Two Gnome-Rhone 14No fourteen-cylinder dual-row air-cooled geared and supercharged engines developing 950 hp each at 12,136 ft (3,700 m). Welded steel-tube mountings attached to front spars of centre-section. Three-bladed controllable-pitch airscrews. Double-walled NACA cowlings. Fuel tanks in wings.
ACCOMMODATION. In nose there was a gun position armed with a machinegun or light automatic canon, and below, a position for the navigator-bomber, provided with transparent panels for forward and downward observation, bomb-sights, releases, etc. Behind this was the wireless-operator's position and installation for camera. Over the leading-edge of the wing was the pilot's compartment seating two in tandem with dual controls. Then followed the internal bomb compartment. Above trailing-edge of wing was a second gunner's position, and below, in the tail of the forward portion and below the after-portion of the fuselage, was a third gunner's position with a complete field of fire aft and below. Passage through the fuselage connected all positions. All positions provided with parachute exits.
Type
5-seat bomber
Engine
2 Gnome-Rhône 14N0/N1 t hree-bladed controllable-pitch airscrews. Double-walled NACA cowlings. Fuel tanks in wings.
Dimensions
Length 14,83 m, height 4,20 m, span 20,58 m, wing area 56,91 m2
Weights
Empty 4350 kg, loaded 8200 kg
Performance
Max. speed 402 km/h, cruising speed 390 km/h, max. range 3200 km, normal range 2000 km service ceiling 8300 m
Armament
1 fixed forward-firing 20 mm Hispano-Suiza HS 404 cannon, 2 rearward firing machine guns. Bombs 1076 kg
Type
Werk.Nr
Registration
History
   
46+21
Second prototype. Captured at Clermont-Ferrand