https://en.wikipedia.org/wiki/Douglas_C-74_Globemaster
The Douglas C-74 Globemaster was a United States heavy-lift cargo aircraft built
by the Douglas Aircraft Company in Long Beach, California. The aircraft was
developed after the Japanese attack on Pearl Harbor. The long distances across
the Atlantic and, especially, Pacific oceans to combat areas indicated a need
for a transoceanic heavy-lift military transport aircraft. Douglas Aircraft
Company responded in 1942 with a giant four-engined design. Development and
production modifications issues with the aircraft caused the first flight to be
delayed until 5 September 1945, and production was limited to 14 aircraft when
the production contract was canceled following V-J Day.
Although not produced in large numbers, the C-74 did fill the need for a
long-range strategic airlifter, in which the subsequent Douglas C-124
Globemaster II was used by the Air Force for many years.
This first flight of a C-74 occurred on 5 September 1945. The first C-74,
42-65402, was airborne just two months after it rolled off the assembly line. At
the time of its first flight, the C-74 was the largest landplane to enter
production, with a maximum weight of 172,000 lb (78,000 kg). It was able to
carry 125 soldiers or 48,150 lb (21,840 kg) of cargo over a range of 3,400 mi
(5,500 km). Perhaps the most notable feature of the C-74 was its cockpit
arrangement with separate canopies over the pilot and copilot; the same
arrangement was used for the XB-42 Mixmaster. This arrangement was unpopular
with flight crews, however, and the aircraft were retrofitted with a more
conventional arrangement. During the life of the aircraft, the radial engines
were also upgraded to 3,250 hp (2,424 kW) Pratt & Whitney R-4360-49 engines. The
aircraft was 31 feet longer than the C-54 Skymaster, and would be 24 feet longer
than the proposed C-118 Liftmaster.
With the need for military aircraft greatly reduced by the end of World War II,
the order for 50 military aircraft was canceled in January 1946 after production
of only 14 aircraft. This cancellation also ended plans to build an airliner
version of the C-74 for the civilian market, as the limited military production
run increased the cost per civilian aircraft to over $1,412,000 and Pan American
canceled its order. Douglas then canceled the DC-7 designation. The DC-7
designation was later used for a completely different civilian airliner project
in the early 1950s, having no relationship to the C-74.
Role
Strategic airlifter
Manufacturer
Douglas Aircraft Company
First flight
5 September 1945
Retired
1970s
Status
Retired
Primary users
United States Army Air Forces
United States Air Force
Produced
Number built
14 (one converted to C-124 prototype)
Developed into
C-124 Globemaster II
Of the 14 Globemasters built, 11 actually saw operational service. All were used
by the United States Army Air Forces Air Transport Command (ATC), and later by
the United States Air Force Military Air Transport Service (MATS).
The C-74 had a crew of five, including copilot, pilot, radio operator,
navigator, and flight engineer. Crew rest quarters were included for
long-duration missions. Passageways were provided in the wing to permit the
flight engineer to perform servicing and repairs while in flight. It could carry
125 fully equipped troops, 115 litter patients with their medical attendants, or
up to 50,000 lb (22,700 kg) of cargo. The cargo bay had twin hoists that could
be moved on a rail up and down the bay. They could be used to drop a removable
belly section to ease loading of cargoes, reducing the need for specialized
cargo handling equipment.
The small numbers of C-74s built meant that the aircraft's service was limited,
but it gave the Air Force experience with the operation and utility of large
transport aircraft.
Specifications (C-74 Globemaster)
General characteristics
Crew: 5
Capacity: 125 troops
Payload: 48,150 lb (21,840 kg)
Length: 124 ft 2 in (37.85 m)
Wingspan: 173 ft 3 in (52.81 m)
Height: 43 ft 9 in (13.34 m)
Empty weight: 86,172 lb (39,087 kg)
Loaded weight: 154,128 lb (69,911 kg)
Max. takeoff weight: 172,000 lb (78,000 kg)
each
Performance
Maximum speed: 328 mph (285 kn, 528 km/h) at 10,000 ft (3,050 m)
Range: 3,400 mi (2,950 nmi, 5,470 km)
Service ceiling: 21,300 ft (6,490 m)
Rate of climb: 2,605 ft/min (13.2 m/s)
Power/mass: 0.08 hp/lb (140 W/kg)
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