C-17
GENERAL DESCRIPTION: The C-17 Globemaster III is a high-wing, four-engine, T-tailed military transport.
EXTERNAL DIMENSIONS
Wingspan to winglet tip
169.8 feet (51.76 m)
Length
174 feet (53.04 m)
Height at tail
55.1 feet (16.79 m)
Fuselage diameter
22.5 feet (6.86 m)
ENGINES
Four Pratt & Whitney PW2040 (military designation F117-PW-100) 40,440 pounds thrust each
CARGO COMPARTMENT
Cargo compartment crew
One loadmaster
Cargo floor length
68.2 feet (20.78 m)
Ramp length
19.8 feet (6.04 m)
Loadable width
18 feet (5.49 m)
Loadable height
12.3 feet (3.76m) under wingbox
14.8 feet (4.50m) aft of wingbox
Ramp to ground angle
9 degrees
Ramp capacity
40,000 lbs. (18,144 kg)
Aerial delivery system capacity
Pallets
Eleven 463L pallets (including 2 on ramp)
Single load airdrop
60,000 pound platform (27,216 kg)
Sequential loads airdrop
110,000 pounds (49,895 kg)
(60 feet of platforms) (18.29 m)
Cargo handling system
Eighteen 463L Pallets (including 4 on ramp)
Combat offload
All pallets from aerial delivery or cargo handling systems
SEATING
Sidewall (permanently installed)
54 (27 each side, 18 inches wide, 24 inch spacing center to center)
Centerline (stored on board)
48 (8 sets of six back-to-back)
Palletized (10-passenger pallets)
90 on 9 pallets, plus 54 passengers on sidewall seats
AEROMEDICAL EVACUATION
Litter stations (onboard)
Three (3 litters each)
Litter stations (additional kit)
Nine
Total capability (contingency)
36 litters, 102 ambulatory
COCKPIT
Flight crew
2 pilots
Observer positions
2
Instrument displays
2 full-time, all-function, head-up displays (HUD), 4 multi-function cathode-ray tube displays plus conventional instruments as backup
Navigation system
Digital electronics
Communication
Integrated radio management system
Flight controls system
Quad-redundant electronic flight control with mechanical actuated backup system
WING
Area
3,800 sq. ft. (353.03 sq. m)
Aspect Radio
7.165
Wing sweep angle
25 degrees
Airfoil type
Supercritical
Flaps
Fixed-vane, double-slotted, simple-hinged
WINGLET
Height
8.92 feet (2.72 m)
Span
9.21 feet (2.81 m)
Area
35.85 sq. ft. (3.33 m)
Sweep
30 degrees
Angle
15 degrees from vertical
HORIZONTAL TAIL
Area
845 sq. ft. (78.50 sq. m)
Span
65 feet (19.81 m)
Aspect ratio
5.0
Sweep
27 degrees
LANDING GEAR
Main, type
Twin-strut tandem per side of aircraft, three wheels each strut
Width (outside to outside)
33.7 feet (10.27 m)
Tires
50x21-20
Nose, type
Single strut, steerable with dual wheels
Tires
40 x 16 - 14
Wheelbase
65.8 feet (20.06 m)
C-5
Primary Function: strategic airlift.
Contractor: Lockheed-Georgia Co.
Length: 247 feet, 10 inches (75.3 meters).
Height At Tail: 65 feet, 1 inch (19.8 meters).
Wingspan: 222 feet, 9 inches (67.9 meters).
Stabilizer Span: 68 feet, 9 inches (20.8 meters).
Cargo Compartment Height: 13 feet, 6 inches (4.10 meters); width 19 feet (5.76 meters).
Maximum Takeoff Weight: 769,000 pounds (346,500 kilograms).
Maximum Wartime Takeoff Weight: 840,000 pounds (378,000 kilograms).
Operating Weight: 374,000 lb
Max Payload: 2.5g 216,000 lb
Max Payload: 2.25g 261,000 lb
Load: 291,000 pounds (130,950 kilograms) maximum wartime payload.
Power Plant: Four General Electric TF39-GE-1C turbofan engines.
Thrust: 41,000 pounds (18,450 kilograms), each engine.
Takeoff/Landing Distances: 12,200 feet (3,697 meters) takeoff fully loaded;
4,900 feet (1485 meters) land fully loaded.
Total Fuel Capacity: 51,154 US gal
Max Payload Range: 2,960 NM
Range: 5,940 miles (5,165 nautical miles) empty.
Ferry Range: 6,985 NM
Speed: 541 mph (Mach 0.72)
Design Cruise Speed: 489 kt
Long Range Cruise Speed: 465 kt
Max Rate of Climb (MGW): 1,610 fpm
Max Operating Altitude: 43,500 ft
Ceiling: 34,000 feet (10,303 meters) with a 605,000-pound (272,250-kilogram) load.
Accommodations: Upper deck seats 73 passengers; forward upper deck seats six, a relief crew of seven, and eight mail or message couriers. The flight deck has work stations for the entire crew. The upper deck's forward and rear compartments have galleys for food preparation and lavatories.
Sensors: An automatic trouble-shooting system constantly monitors more than 800 test points in the various subsystems of the C-5. The Malfunction Detection Analysis and Recording System uses a digital computer to identify malfunctions in replaceable units. Failure and trend information is recorded on magnetic tape for analysis by maintenance people.
Unit Cost: C-5A, $163.4 million; C-5B, $167.7 million
Crew: Six (pilot, co-pilot, two flight engineers, two loadmasters)
Date Deployed December: 1969 (for training); June 1970 (operational); December 1984 (to Reserve).
Inventory Active-force, 70; ANG, 11; Reserve, 28