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help during the development of LEDFAA 1.3. The contents of the paper reflect the views of the authors, who are
responsible for the facts and accuracy of the data presented within. The contents do not necessarily reflect the
official views and policies of the FAA. The paper does not constitute a standard, specification, or regulation.
LIST OF FIGURES
1. Visible changes to the user interface in the Startup window (metric option and changeable working directory).
2. LEDFAA 1.2 failure model showing full-scale test data and model curves for four subgrade modulus values.
3. LEDFAA 1.3 failure model showing full-scale test data and separate model curves for high and low coverages.
4. Equivalent tire width at the top of the subgrade with no overlap (two equivalent tires).
5. Equivalent tire width at the top of the subgrade with overlap (one equivalent tire).
6. Tandem gear factor as a function of tandem spacing for two wheels in tandem (the maximum gear factor is the
number of wheels in tandem for other gears, e.g. 3 for a triple-dual-tandem such as a B-777).
7. Vertical subgrade strain evaluation points for B-747-400, all 16 wheels contribute to the strain computation at
each evaluation point.
8. Vertical subgrade strain evaluation points for A380-800, all 20 wheels contribute to the strain computation at
each evaluation point.
REFERENCES
1. Federal Aviation Administration, Office of Airport Safety and Standards, “Airport Pavement Design for the
Boeing 777 Airplane,” Advisory Circular AC 150/5320-16, U.S. Department of Transportation, 1995.
2. Federal Aviation Administration, Office of Airport Safety and Standards, “Airport Pavement Design and
Evaluation,” Advisory Circular AC 150/5320-6D, U.S. Department of Transportation, 1995 (also see
http://www.faa.gov/arp/150acs.htm for updates).
3. Horonjeff, Robert and Francis X. McKelvey, Planning and Design of Airports, Third Edition, McGraw-Hill
Book Company, 1983.
4. Barker, Walter R., and William N. Brabston, “Development of a Structural Design Procedure for Flexible Airport
Pavements,” Report No. FAA-RD-74-199, U.S. Department of Transportation, Federal Aviation Administration,
September 1975.
5. Parker, F., Jr., W.R. Barker, R.C. Gunkel, and E.C. Odom, “Development of a Structural Design Procedure for
Rigid Airport Pavements,” Report No. FAA-RD-77-81, U.S. Department of Transportation, Federal Aviation
Administration, April 1977.
6. Rollings, R.S., “Design of Overlays for Rigid Airport Pavements,” Report No. DOT/FAA/PM-87/19, U.S.
Department of Transportation, Federal Aviation Administration, April 1988.
7. Hayhoe, Gordon F., “LEAF – A New Layered Elastic Computational Program for FAA Pavement Design and
Evaluation Procedures,” 2002 FAA Airport Technology Transfer Conference, Atlantic City, New Jersey, May 5-
8, 2002.
8. Barker, W.R., and C.R. Gonzalez, “Pavement Design by Elastic Layer Theory,” Proceedings, ASCE Conference
on Aircraft/Pavement Interaction, Kansas City, 1991.
9. Barker, W.R., and C.R. Gonzalez, “Super-Heavy Aircraft Study,” Technical Report GL-94-12, U.S. Army Corps
of Engineers, Waterways Experiment Station, April 1994.
10. Holliway, Robert, and K. Stuart Millard, “Aircraft Characteristics for Airfield Pavement Design and
Evaluation,” Air Force Engineering and Services Center, Tyndall Air Force Base, Florida, August 1990.
11. Brill, David R., Edward H. Guo, and Lia Ricalde, “Three-Dimensional Finite Element Analysis of Multiple
Aircraft Gear Loadings on Rigid Airfield Pavements,” Proceedings of the Third International Symposium: 3D
Finite Elements for Pavement Analysis, Design and Research, 2–5 April, 2002, Amsterdam, Netherlands.
8
FIGURE 1 Visible changes to the user interface in the Startup window (metric option and changeable
working directory).
9
SUBGRADE VERTICAL STRAIN & NUMBER OF COVERAGES
ONLY SUBGRADE FAILURE CONSIDERED
y = 0.005x-0.1149
R2 = 0.6906
0.0001
0.001
0.01
1 10 100 1,000 10,000 100,000 1,000,000
No. of Coverages to Failure
Vertical Subgrade Strain, inch/inch
Stockton - 8
MWHGL - 7
Structural Layers Study - 6
NAPTF - 9
CC1-MFC-4W
CC1-MFC-6W
CC3-LFC1-6W
CC3-LFC1-4W
CC3-LFC2-6W
CC3-LFC2-4W
CC3-LFC3-6W
CC3-LFC3-4W
CC1-MFS-4W
CC1-MFS-6W
SG Mod. = 4,500
SG Mod. = 9,000
SG Mod. = 15,000
SG Mod. = 22,500
FIGURE 2 LEDFAA 1.2 failure model showing full-scale test data and model curves for four subgrade
modulus values.
10
SUBGRADE VERTICAL STRAIN & NUMBER OF COVERAGES
ONLY SUBGRADE FAILURE CONSIDERED
　
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