| . |





**Data for each of these
characteristics can be
obtained by contacting
the EICO
Aviation Specialist
at the NAVFAC Criteria
Office.
|

The
C-17 Globemaster III is the newest, most flexible cargo aircraft to
enter the airlift force. The C-17 is capable of rapid strategic delivery
of troops and all types of cargo to main operating bases or directly
to forward bases in the deployment area. The aircraft is also capable
of performing tactical airlift and airdrop missions when required. The
inherent flexibility and performance of the C-17 force improve the ability
of the total airlift system to fulfill the worldwide air mobility requirements
of the United States. The ultimate measure of airlift effectiveness
is the ability to rapidly project and sustain an effective combat force
close to a potential battle area. Threats to U.S. interests have changed
in recent years, and the size and weight of U.S.-mechanized firepower
and equipment have grown in response to improved capabilities of potential
adversaries. This trend has significantly increased air mobility requirements,
particularly in the area of large or heavy outsize cargo. As a result,
newer and more flexible airlift aircraft are needed to meet potential
armed contingencies, peacekeeping or humanitarian missions worldwide.
The C-17 is capable of meeting today’s demanding airlift missions.
|
|
Aircraft Type |
Cargo
and Troop Transport
|
|
Aircraft Manufacturer
|
Boeing
Company [McDonnell Douglas Corp.]
|
Engine Manufacturer |
Pratt
& Whitney
|
Engine Number |
F117-PW-100
|
Type of Landing Gear |
Twin Tandem Tricycle
|
Design Gear Load |
|
Design Tire Pressure |
142 psi
|
Pass/Cov Ratio Channelized |
1.38
|
|
Pass/Cov Ratio Unchannelized
|
1.91
|
|
|
Wingspan |
169 ft 10 in
|
Length (Overall) |
174 ft
|
Height (Overall) |
55 ft 1 in
|
Wheelbase |
65 ft 9.5 in
|
Nose to centerline of main gear |
|
|
Wheel track (tread) Main
|
33 ft 8.5 in
|
|
Wheel track (tread) Nose
|
|
Vertical clearance of wingtip at
maximum weight |
13 ft 6 in
|
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 |
114 ft
|
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 |
331.4 klbs
|
Min takeoff distance with min
takeoff weight |
3,000 ft
|
Min takeoff distance with min
takeoff weight with abort distance |
**
|
Max takeoff weight at peace-time |
580.0 klps
|
Max takeoff weight at war-time |
580.0 klps
|
Min takeoff distance with max
takeoff weight |
7,600 ft
|
Min landing weight |
444.1 klps
|
Max landing weight |
580.0 klps
|
Corner |
|
Field |
|
|
Peace-time weight used for pavement evaluation
|
|
Min landing distance at min landing
weight
|
|
|
Min landing distance at max landing
weight
|
2,700 ft
|
View / Sort aircraft on Spreadsheet.
|