| . |
**Data for each of these
characteristics can be
obtained by contacting
the EICO
Aviation Specialist
at the NAVFAC Criteria
Office.
|
 Designed to meet a US Air Force requirement for a large troop-carrying aircraft with global range, the C-141 can hold up to 154 troops or 123 paratroopers. The design features high mounted wings to maximize cargo space as well as clamshell doors at the rear fuselage for loading and unloading. The new aircraft proved very useful in Vietnam, but the Air Force soon realized that the C-141 was capable of carrying much greater loads than could physically fit within the aircraft. Lockheed was then contracted to convert some 270 aircraft to the C-141B standard with a fuselage extension and in-flight refueling capability. Nearing the end of its service life, the C-141 is being supplemented and eventually replaced by the C-17.
|
|
Aircraft Type |
Cargo
and Troop Transport
|
|
Aircraft Manufacturer
|
Lockheed-Georgia
Co.
|
Engine Manufacturer |
Pratt
& Whitney
|
Engine Number |
TF-33-P-7
|
Type of Landing Gear |
Dual Tandem Tricycle
|
Design Gear Load |
155,000 lbs
|
Design Tire Pressure |
180 psi
|
Pass/Cov Ratio Channelized |
3.49
|
|
Pass/Cov Ratio Unchannelized
|
6.25
|
|
|
Wingspan |
160 ft
|
Length (Overall) |
168.3 ft
|
Height (Overall) |
39.6 ft
|
Wheelbase |
56.56 ft
|
Nose to centerline of main gear |
74 ft 9 in
|
|
Wheel track (tread) Main
|
20.92 ft
|
|
Wheel track (tread) Nose
|
|
Vertical clearance of wingtip at
maximum weight |
|
Centerline of fuselage to
approximate pivot point based on maximum
steering angle or locked wheels |
|
Height of jet engine on
centerline of fuselage |
|
|
|
Minimum turning radius |
120 ft 4 in
|
Engine operating danger areas -
idle |
|
Ground clearance |
**
|
Electrical Service |
• Maximum kVa by aircraft
for 400Hz distribution |
|
Mechanical Service |
• Air starting system |
|
• Preconditioned air |
|
• Environmental control air |
|
|
|
Min takeoff weight |
144.5 klbs
|
Min takeoff distance with min
takeoff weight |
|
Min takeoff distance with min
takeoff weight with abort distance |
**
|
Max takeoff weight at peace-time |
325.0 klbs
|
Max takeoff weight at war-time |
344.9 klbs
|
Min takeoff distance with max
takeoff weight |
|
Min landing weight |
140.0 klbs
|
Max landing weight |
323.0 klbs
|
|
Peace-time weight used for pavement evaluation
|
|
• Min landing distance at min landing
weight
|
|
|
• Min landing distance at max landing
weight
|
|
View / Sort aircraft on Spreadsheet.
|
