Cessna 140

https://en.wikipedia.org/wiki/Cessna_140

The Cessna 120, 140, and 140A, are single-engine, two-seat, conventional landing
gear (tailwheel), light general aviation aircraft that were first produced in
1946, immediately following the end of World War II. Production ended in 1951,
and was succeeded in 1959 by the Cessna 150, a similar two-seat trainer which
introduced tricycle gear. Combined production of both aircraft was 7,664 units
in five years.

Cessna 140

The Cessna 140 was originally equipped with a Continental C-85-12 or C-85-12F
horizontally opposed, air-cooled, four-cylinder piston engine of 85 hp (63 kW).
The Continental C-90-12F or C-90-14F of 90 hp (67 kW) was optional, as was the
108 hp (81 kW) Lycoming O-235-C1 engine, an aftermarket installation authorized
in the type certificate. This model had a metal fuselage and fabric wings with
metal control surfaces. The larger Cessna 170 was a four-seat 140 with a more
powerful engine.

Cessna 120

The Cessna 120 was an economy version of the 140 produced at the same time. It
had the same engine as the 140, but lacked wing flaps. The rear-cabin "D" side
windows and electrical system (radios, lights, battery and starter) were
optional. A 120 outfitted with every factory option would be nearly equivalent
to a 140, but the International Cessna 120/140 Association believes that no 120s
were originally built this way. Despite this, many decades' worth of owner-added
options have rendered many 120s almost indistinguishable from a 140 aside from
the absence of wing flaps. The 120 was dropped from production upon introduction
of the 140A in 1949.

Cessna 140A

In 1949, Cessna introduced the 140A, a new variant with aluminum-covered wings
and single wing struts instead of the fabric wing covering, dual "V" struts, and
jury struts fitted on earlier models. Standard engines were the Continental
C-90-12F or C-90-14F of 90 hp (67 kW), with the 85 hp (63 kW) Continental
C-85-12, C-85-12F, or C-85-14F engines optional. The spring-steel gear had been
swept 3 in (8 cm) forward on 120 and 140 models in late 1947 so wheel extenders
were no longer necessary to counter nose-over tendencies during heavy
application of brakes; all 140A models had the improved gear legs. Despite these
improvements, sales of the 140 lineup faltered, and the 140A comprised only
seven percent of overall 120/140 production.


Role
Light utility aircraft

Manufacturer
Cessna Aircraft Company

First flight
June 28, 1945 (140)
1946 (120)

Introduction
1946

Produced
1946-1951

Number built
7,664

Unit cost

US$3495 (Cessna 140 in 1946)

Common modifications to the Cessna 120 and 140 include:

"Metalized" wings, where the fabric is replaced with light-gauge sheet aluminum,
eliminating the need to periodically replace the wing fabric.

The installation of landing gear extenders to reduce the tendency of the
aircraft to nose over on application of heavy braking. These were
factory-optional equipment.

Installation of rear-cabin "D" side windows on 120s that were not originally so
equipped.

Installation of electrical systems on 120s that were not originally so equipped,
allowing owners to install an electric starter, more sophisticated avionics
and/or lights for night flying.

Installation of a more powerful engine. A popular conversion today is to replace
the original C-85 or C-90 with a 100 hp (75 kW) Continental O-200. A kit is
available to install a Lycoming O-320 but this conversion is less prevalent due
to a roughly 100 lb (45 kg) weight penalty and a sharp increase in fuel
consumption.

Specifications (Cessna 140)

General characteristics
Crew: one
Capacity: one passenger
Length: 21 ft 6 in (6.55 m)
Wingspan: 33 ft 4 in (10.16 m)
Height: 6 ft 3 in (1.91 m)
Wing area: 159.3 sq ft (14.80 m2)
Empty weight: 890 lb (404 kg)
Gross weight: 1,450 lb (658 kg)
Fuel capacity: 25 US gallons (95 litres)
Powerplant: 1 × Continental C-85 four cylinder, four stroke, horizontally
opposed aircraft engine, 85 hp (63 kW)
Propellers: 2-bladed Sensenich

Performance
Maximum speed: 125 mph (201 km/h; 109 kn)
Cruise speed: 105 mph (169 km/h; 91 kn)
Stall speed: 45 mph (72 km/h; 39 kn) flaps down
Never exceed speed: 140 mph (225 km/h; 122 kn)
Range: 450 mi (391 nmi; 724 km)
Service ceiling: 15,500 ft (4,700 m)
Rate of climb: 680 ft/min (3.5 m/s)
Wing loading: 9.1 lb/sq ft (44 kg/m2)




*